MD Helicopters MILVIZ MD530F Rotorcraft Flight Manual Download Page 274

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FAA Approved

Revision 6

−

MD 500
(Models 369HE/HS/HM

)

ROTORCRAFT FLIGHT MANUAL

CSP

−

HE/HS

−

Optional Equipment

Anti

−

Ice Airframe Fuel Filter

FIRE

FILTER BOWL

Preflight Checks:

PART IV

NORMAL PROCEDURES

BATTERY/EXT PWR switch

AS REQUIRED

Start pump

WARNING

Do not open drain valve unless start pump is ON. An unexpected
flameout or power loss may occur if air is allowed to enter the fuel
system.

NOTE

If aircraft has been exposed to freezing temperatures, failure to drain may be due

to ice in filter element.

Drain filter from valve on bottom of filter unit.

NOTE

The following checks should be performed as part of the engine compartment

checks listed in the basic preflight checklist in Section IV.

Start pump

OFF

TEST BUT-
TON

WALL

ANTI−ICE DRAIN
VALVE

F01

−

072

Figure 9

−

3. Anti

−

Ice Airframe Fuel Filter

Summary of Contents for MILVIZ MD530F

Page 1: ... MD530FModel R O T O R C R A F T F L I G H T M A N U A L REGISTRATION NO SERIAL NO i ...

Page 2: ... you up on our forums and you may ask post your question problem there So on to how to get this bird in the air The first thing that you need to do is to run the ACM The ACM is a program that contains all of the available parameters for the aircraft This program is on your desktop and looks like this Once you ve double clicked on this icon you will be taken to the MV Manager This is where you can ...

Page 3: ...rent If it s the only one Please go and buy more Once you have selected the MD530F you will be presented with the actual ACM of the aircraft Before it runs it will probably ask you to accept running this program Please click RUN See pic here ...

Page 4: ...ve and pick the state of the aircraft You may do this differently on each and every livery that you have added It s important to note that your default aircraft SHOULD be the Default C172 with all systems off This allows the aircraft to set itself up properly If you have purchased any addon packs from us Mindstar GPS F1 GTN s or the MV Addons you can use page 2 for adding or removing these See pic...

Page 5: ...ly on the ACM you are now Ready To Fly and you may move the collective up and away you go If on the other hand you have chosen Cold and Dark on the ACM You will have to start it up and then you can fly away This helicopter unlike the MV407 that we recently released doesn t have FADEC What this means is that you will have to watch your temperatures and your RPMs as well as your Torque to make sure ...

Page 6: ... released You may get a little nervous during the initial light off and back the throttle off which causes the fire to go out Not a big deal as long as the starter is still motoring just embarrassing You may do a restart For a Full Checklist see here http www milviz com manuals 1 jpg http www milviz com manuals 2 jpg We have included for you in this package the actual manual for a MD530F Do note t...

Page 7: ... are manual The helicopter is equipped with Honeywell dual KX175 navigation system receivers and Honeywell formerly Allied Signal KR 85 automatic direction finder night flying lighting attitude and directional gyroscopes and a rate climb indicator An alternative avionics fit includes a Rockwell Collins VHF 251 231 navigation receiver fitted with an IND 350 navigation indicator and an ADF 650 autom...

Page 8: ...void range is to be accomplished as quickly as possible Maximum allowable time in the speed avoid range is 1 minute NOTE Refer to Rolls Royce CEB A 1400 Engine oil system limits Flight operation temperature limits 0 C to 107 C NOTE These engine oil temperature limits pertain to all gauge configurations 0 C is when the needle is at the bottom of the yellow green arc Flight operation pressure limits...

Page 9: ...s 1 6 1 10 Technical Publications 1 9 1 11 Design and Construction 1 10 1 12 General Dimensional Data 1 13 1 13 Capacities Fuel System 1 14 1 14 Conversion Charts Tables 1 15 SECTION II LIMITATIONS 2 1 Flight Restrictions 2 1 2 2 Environmental Operating Conditions 2 3 2 3 Airspeed Limitations 2 3 2 4 Weight Limitations 2 6 2 5 Rotor Brake Limitations If Installed 2 8 2 6 Rotor Speed Limits Allison...

Page 10: ...MV MD530F ROTORCRAFT FLIGHT MANUAL n 250 C20 2 10 ...

Page 11: ...3 1 3 2 Warning and Caution Indicators 3 2 3 3 Engine Failure 3 3 3 4 Air Restart Engine 3 6 3 5 Low Rotor Speed 3 7 3 6 Emergency Landing Procedures 3 7 3 7 Fire 3 9 3 8 Engine Fuel Control System Malfunctions 3 14 3 9 Other Engine Caution Indications 3 16 3 10 Main Rotor and Tail Rotor Transmission Malfunctions 3 17 3 11 Flight Control Malfunctions 3 19 3 12 Abnormal Vibrations 3 13 Fuel System ...

Page 12: ...mergency Equipment SECTION IV NORMAL PROCEDURES1 3 29 4 1 Preflight Requirements Daily Preflight Checks 4 1 4 3 4 2 Engine Pre Start Cockpit Check 4 12 4 3 Engine Start 4 15 4 4 Engine Run Up 4 17 4 5 Before Takeoff 4 19 4 6 Takeoff 4 7 Cruise 4 19 4 21 4 8 Low Speed Maneuvering 4 21 ...

Page 13: ...duction Procedures 4 28 SECTION V PERFORMANCE DATA 5 1 General 5 1 5 2 Airspeed Calibration Curve 5 2 5 3 Density Altitude Chart 5 4 5 4 Speed for Best Rate of Climb 5 6 5 5 Height Velocity Diagram Gross Weight Limits for Height Velocity Diagram 5 8 5 6 Hover Ceiling vs Temperature IGE 5 11 5 7 Power Check Chart Allison 250 C18 Engine 5 8 Power Check Chart Allison 250 C20 Engine 5 29 5 32 SECTION ...

Page 14: ...guration 6 12 6 5 Longitudinal Loading of Cargo 6 14 6 6 Permissible Lateral Loadings 6 7 Lateral Loading of Cargo 6 16 6 16 6 8 Internal Loading of Cargo 6 20 SECTION VII HANDLING SERVICING AND MAINTENANCE 7 1 Helicopter Components 7 2 Use of External Power 7 1 7 1 7 3 Hoisting Jacking and Lifting 7 1 ...

Page 15: ...or and Rotor Blades 7 15 7 15 Cleaning Transparent Plastic 7 15 7 16 Fluid Leak Analysis 7 15 7 17 Main Rotor Blade Leading Edge Abrasion Tape 7 16 7 18 Preservation and Storage 7 16 7 19 Flyable Storage No Time Limit 7 17 7 20 Engine Compressor Wash 7 18 SECTION VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA 8 1 General SECTION IX OPTIONAL EQUIPMENT 8 1 9 1 General Information 9 1 9 2 Listing Op...

Page 16: ... blank 9 8 Operating Instructions Engine Air Inlet Deflector 9 21 9 9 Operating Instructions Emergency Floats 9 23 9 10 Operating Instructions Rotorcraft Hoist 9 29 9 11 Operating Instructions Rotorcraft Litter 9 35 9 12 Operating Instructions Luggage Pod 9 43 ...

Page 17: ... MANUAL Revision 5 F vii F viii blank PARAGRAPH PAGE 9 13 Operating Instructions Search Light 9 45 9 14 Operating Instructions Utility Floats 9 47 9 15 Operating Instructions Automatic Reignition 9 16 369HM Configuration 9 51 9 5 ...

Page 18: ...7 Method of Presentation 1 5 1 8 Definition of Terms 1 5 1 9 Abbreviations 1 6 1 10 Technical Publications 1 9 1 11 Design and Construction 1 10 1 12 General Dimensional Data 1 13 Figure 1 1 MD 500 Helicopter Principal Dimensions 1 13 1 13 Capacities Fuel System 1 14 1 14 Conversion Charts Tables 1 15 Figure 1 2 Speed MPH Knots KmH 1 15 Figure 1 3 Temperature Conversion Chart 1 16 Table 1 1 Liquid...

Page 19: ... Linear Measure In Cm Inches to Centimeters 1 17 Table 1 3 Linear Measure Ft M Feet to Meters 1 18 Table 1 4 Weight Lb Kg Pounds to Kilograms 1 18 Figure 1 4 Conversion Chart Knots Meters Second 1 19 Table 1 5 Standard Atmosphere Table 1 20 ...

Page 20: ...e sure to select the appropriate data for model type and engine installed 1 2 SCOPE This manual meets all FAA requirements for APPROVED DATA and that data is so designated MDHI has included additional supplemental data which is intended to provide the pilot with information that enhances and eases his task 1 3 HELICOPTER CERTIFICATION The helicopter is certified by the Federal Aviation Administrat...

Page 21: ... FAA approved for the 369HE HS may be installed and used 1 5 PILOT S BRIEFING Prior to flight passengers should be briefed on the following Approach and depart the helicopter from the front in full view of the pi lot being aware of the main rotor Use of seat belts and shoulder harnesses Smoking The opening and closing of doors Evacuation of the aircraft in an emergency Location and use of emergenc...

Page 22: ...craft and general rotorcraft information and conversion charts SECTION II LIMITATIONS FAA Approved Specifically defines the limiting factors procedures and parameters within which the rotorcraft may be operated FAA regulations require that limita tions not be exceeded SECTION III EMERGENCY AND MALFUNCTION PROCEDURES FAA Approved Problems which could be encountered in flight are defined and the pro...

Page 23: ...h which the pilot may have direct involvement either while at his normal base of operations or in the field SECTION VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA The information provided in Section VIII is given by the manufacturer to further assist the pilot in obtaining maximum utilization of the rotorcraft SECTION IX OPTIONAL EQUIPMENT FAA Approved Certain optional equipment is available for ...

Page 24: ...nates the latest new or changed information appearing on that page A hand points to changes in the contents of an illustration 1 8 DEFINITION OF TERMS The concepts of procedural word usage and intended meaning that have been adhered to in preparing this manual is as follows Shall has been used only when the application of a procedure is mandatory Should has been used only when the application of a...

Page 25: ... BL Butt Line C C Celsius CAB Cabin CAB HEAT Cabin Heat CAUT Caution CG Center of Gravity CKP T Cockpit Cm Centimeters COM Communication CCW Counter Clockwise CW Clockwise D DC Direct Current DIR Direction Directional E ENG Engine EXT Extend External F F Fahrenheit FAA Federal Aviation Administration FAR Federal Aviation Regulation FS Fuselage Station Ft Foot Feet G GAL Gallons GEN Generator GPU G...

Page 26: ...IMC Instrument Meteorological Conditions IMP Imperial INST Instrument In Inches INST R Instrument IVSI Instantaneous Vertical Speed Indicator K Kg Kilogram KCAS Knots Calibrated Airspeed KG Kilogram s KIAS Knots Indicated Airspeed Km Kilometer KmH Kilometers per Hour KTAS Knots True Airspeed L L Left Liters LAT Lateral Lb s Pound s LND Landing LONG Longitudinal LT Light M M Meters MAN Manual Mbar ...

Page 27: ...ch PWR Power Q QTY Quantity R R Right REL Release RET Retract RPM Revolutions per Minute RTR Rotor S Sec Seconds SHP Shaft Horsepower SL Sea Level STBY Standby STA Station STC Supplemental Type Certificate SYS System T TOP Takeoff Power U U S United States V VFR Visual Flight Rules VH Maximum speed in level flight at MCP VLV Valve VMC Visual Meteorological Conditions VNE Never Exceed Speed Vs Vers...

Page 28: ...n and examined against the List of Effective Pages Reissues Occasionally the manual may be reissued and is identified as Reissue 1 Reissue 2 etc The preceding issue of the manual then becomes ob solete and must be discarded The reissue includes all prior revisions All pages in a reissue become Original pages The reissue may also include new or changed data These changes will be identified on the S...

Page 29: ... a two bladed semi rigid type Power from the turboshaft engine is transmitted through the drive shafts to the main and tail rotor transmissions An overrunning one way clutch placed between the en gine and main rotor transmission permits free wheeling of the rotor system during autorotation The airframe structure is egg shaped and provides very clean aerodynamic lines The rigid three dimensional tr...

Page 30: ...e compartment is provided through clamshell doors contoured to the shape the fuselage The lower section is divided by the center beam and provides a housing for the two fuel cells Provisions for the attachment of a cargo hook are located on the bottom of the fuselage in line with the center beam Four doors are installed on the helicopter two on each side The two forward doors permit access to the ...

Page 31: ... helicopters use torsion tension straps in lieu of thrust bearing stacks to contain blade centrifugal loading and allow feathering the MDHI strap pack arrangement goes three steps further First the strap configuration while secured firmly to the hub actually allows the centrifugal load exerted by one blade to be countered by the force exerted by the opposite blade Thus very light centrifugal loads...

Page 32: ... 59 4 572 6 477 7 010 8 025 9 235 1 12 GENERAL DIMENSIONAL DATA 4 57 ft 1 39 m 26 33 ft 8 02 m 5 06 ft 1 54 m NOTE ADD 0 63 FOOT 0 19 METER TO ALL VERTICAL DIMENSIONS IF EXTENDED GEAR IS INSTALLED 30 30 ft 9 23 m 21 25 6 47 m 23 00 ft 7 01 M 15 00 ft 4 57m 8 20 ft 2 50 m 0 79 ft 7 20 ft 2 20 m 7 00 ft 2 13 m 6 30 4 25 ft 8 50 ft 2 59 m 0 24 m 1 92 m 1 29 m 6 80 ft 2 07 m Figure 1 1 MD 500 Helicopt...

Page 33: ...s 421 6 pounds Usable fuel is 59 9 U S gallons 226 8 liters 407 5 pounds JET B Standard non self sealing tanks Capacity is 64 0 U S gallons 242 liters 416 0 pounds Usable fuel is 63 4 U S gallons 240 liters 412 1 pounds Optional self sealing tanks Capacity is 62 0 US gallons 234 liters 402 0 pounds Usable fuel is 59 9 U S gallons 232 liters 389 5 pounds CAPACITIES OIL Engine oil 3 0 US quarts 2 84...

Page 34: ...TER CHART AT 100 KNOTS AND FOLLOW ARROW TO SLOPING LINE TO FIND MPH MOVE LEFT AND READ 115 MPH TO FIND KM HR MOVE RIGHT FROM THE SLOPING LINE AND READ 185 KM HR 200 180 160 140 120 100 80 60 40 20 320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0 0 20 40 60 80 100 120 140 160 0 180 KNOTS F05 002 Figure 1 2 Speed MPH Knots KmH ...

Page 35: ... CONVERT F TO C EXAMPLE F C 140 60 120 100 40 KNOWN TEMPERATURE 50 F METHOD ENTER AT 50 F READ 10 C ACROSS ON C SCALE METHOD MAY BE REVERSED TO FIND F WHEN C IS KNOWN ALTERNATE METHOD F 9 5 X C 32 C 5 9 F 32 80 60 40 20 0 20 40 60 80 20 0 20 40 60 F05 003 Figure 1 3 Temperature Conversion Chart ...

Page 36: ...33 367 19 405 04 30 283 68 138 105 99 143 85 181 70 219 56 257 41 295 26 333 12 370 97 408 83 34 069 71 923 109 78 147 63 185 49 223 34 261 19 299 05 336 90 374 76 412 61 Table 1 2 Linear Measure In Cm Inches to Centimeters Inches 0 1 2 3 4 5 6 7 8 9 Cm Cm Cm Cm Cm Cm Cm Cm Cm Cm 0 10 20 30 40 50 60 70 80 90 100 25 40 50 80 76 20 101 60 127 00 152 40 177 80 203 20 228 60 254 00 2 54 27 94 53 34 78...

Page 37: ...23 774 26 822 29 870 32 918 2 743 5 791 8 839 11 887 14 935 17 983 21 031 24 070 27 126 30 174 33 222 Table 1 4 Weight Lb Kg Pounds to Kilograms Pounds 0 1 2 3 4 5 6 7 8 9 Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo 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 4 990 9 525...

Page 38: ...E 35 CONVERT KNOTS TO METERS SEC KNOWN WIND SPEED 25 KT METHOD ENTER CHART AT 25 KT READ APPROXIMATELY 13 METERS SEC ACROSS ON METERS SEC SCALE METHOD MAY BE REVERSED TO FIND KNOTS WHEN METERS SEC ARE KNOWN 30 15 25 20 10 15 10 5 5 0 0 F90 003 Figure 1 4 Conversion Chart Knots Meters Second ...

Page 39: ...3028 1 3246 1 3470 1 3700 1 3935 1 4176 1 4424 1 4678 1 4938 15 00 13 019 11 038 9 056 7 076 5 094 3 113 1 132 0 850 2 831 4 812 6 793 8 774 10 756 12 737 14 718 16 669 18 680 20 662 22 643 24 624 26 605 28 587 30 568 32 549 34 530 59 000 55 434 51 868 48 302 44 735 41 196 37 603 34 037 30 471 26 905 23 338 19 772 16 206 12 640 9 074 5 508 1 941 1 625 5 191 8 757 12 323 15 899 19 456 23 002 26 588...

Page 40: ...d Landing Weight Limitations Helicopters Without Aluminum Tail Rotors 2 6 2 7 2 5 Rotor Brake Limitations If Installed 2 8 2 6 Rotor Speed Limits Allison 250 C18 2 7 Rotor Speed Limits Allison 250 C20 2 8 Power Plant Limits Allison 250 C18 2 8 2 8 2 9 2 9 Powerplant Limitations Allison 250 C20 2 10 2 10 Electrical System Limitations 2 11 2 11 Starter Limitations 2 11 2 12 Fuel System Limitations 2...

Page 41: ... Limitations 7 Instrument Markings Allison 250 C20 Engine 2 15 2 16 2 14 Placards and Decals 2 17 Figure 2 8 VNE Placards Allison 250 C18 Figure 2 9 VNE Placards Allison 250 C20 2 17 2 18 Figure 2 10 Decals and Placards 2 19 FAA Approved Revision 5 2 i 2 ii blank ...

Page 42: ......

Page 43: ...om the left seat The right crew seat may be used for an additional pilot when the approved dual controls are installed Aerobatic flight is prohibited Installed equipment Certification is based on an Engine Failure Warning System including both visual and audio indications and an Outside Air Temperature gauge being installed and operable Flight with doors removed is approved under the following con...

Page 44: ...s 0215E and prior that have not been modified VNE is 85 knots IAS See Sec IV Doors Off Flight for interior configuration changes required WARNING Any object that is not properly secured may exit the aircraft during flight Items secured with Velcro tape should not be considered properly secured see Section IV Doors Off Flight Flight with the center seat occupied Dual controls removed refer to the H...

Page 45: ...ly to 6000 feet pressure altitude at a maximum temperature of 35 C 95 F varying linearly to 20 000 feet pressure altitude at a temperature 0 C 32 F It is to be assumed that engine air inlet temperature is the same as ambient free air temperature Cold weather operations Flight into known icing conditions is prohibited Flight operation is permitted in falling and or blowing snow only when the Automa...

Page 46: ...d Revision 5 2 4 DENSITY ALTITUDE FEET 20 000 18 000 16 000 GROSS WEIGHT 2000 LB OR LESS 14 000 12 000 10 000 8 000 6 000 4 000 2 000 0 GROSS WEIGHT MORE THAN 2000 LB 0 20 40 60 80 100 120 140 INDICATED AIRSPEED KNOTS F01 008 Figure 2 1 Variation of VNE With Altitude 250 C18 ...

Page 47: ...pproved Revision 5 2 5 DENSITY ALTITUDE FEET 20 000 18 000 16 000 14 000 GROSS WEIGHT 2000 LB OR LESS 12 000 10 000 8 000 6 000 4 000 2 000 0 GROSS WEIGHT MORE THAN 2200 LB 0 20 40 60 80 100 120 140 AIRSPEED KIAS F01 010 Figure 2 2 Variation of VNE with Altitude 250 C20 ...

Page 48: ...equipped with aluminum tail rotors Cargo deck capacity 369HE HS S N 0001 thru 0100 950 LB at 115 pounds per square foot 369HE HS S N 0101 and subsequent 1300 LB at 115 pounds per square foot Utility stowage compartment Maximum weight in the utility stowage compartment is 50 pounds C G limits Table 2 1 Center of Gravity Limits Gross Weight lb Longitudinal C G Limit Sta in Lateral C G Limit Sta in F...

Page 49: ...16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 6 000 5 000 4 000 3 000 2 000 1 000 WEIGHT GREATER THAN 2 550 LB MUST BE JETTISONABLE 0 0 40 30 20 10 0 10 20 AMBIENT TEMPERATURE DEGREES C 40 30 20 10 0 10 20 30 40 50 60 70 AMBIENT TEMPERATURE DEGREES F F01 005 Figure 2 3 Takeoff and Landing Weight Limitations Helicopters Without Aluminum Tail Rotors ...

Page 50: ...her than the full down position during rotor brake application Release rotor brake during the last revolution of the rotor Damage to the rotor blades and drive train can result from sudden CAUTION stoppage of the rotor 2 6 ROTOR SPEED LIMITS ALLISON 250 C18 Maximum RPM Power on 489 RPM Ref 104 percent N2 Minimum RPM Power on 484 RPM Ref 103 percent N2 Maximum RPM Power off 514 RPM Minimum RPM Powe...

Page 51: ...ond During power changes in flight 749 C to 843 C for 6 seconds Gas producer N1 speed limits Maximum continuous 104 Ground idle speed 62 67 NOTE During autorotative flight the N2 governor may reduce N1 below 62 percent Transient limits 105 for 15 seconds N2 limits Normal Power On operation 103 to 104 N2 Transient over speed limit 15 seconds maximum 110 red dot on N2 scale at idle power varying lin...

Page 52: ...s Gas Producer N1 speed limits Maximum continuous 104 Ground idle speed 61 65 Transient limits 104 106 for 15 seconds Power Turbine N2 speed limits Normal Power On operation 103 to 104 N2 Transient overspeed limit 15 seconds maximum 113 at idle power vary ing linearly to 108 at 64 5 psi torque Avoid steady state operations between 75 and 88 Transition through the speed avoid range is to be accompl...

Page 53: ...3 minutes off 2 12 FUEL SYSTEM LIMITATIONS Fuel Specifications For additional information on fuels refer to the appropriate Rolls Royce Opera tion and Maintenance Manual Primary Jet A ASTM D 1655 Jet A 1 ASTM D 1655 Jet B ASTM D 1655 JP 1 conforming to ASTM D 1655 Jet A or Jet A 1 JP 4 MIL DTL 5624 JP 5 MIL DTL 5624 JP 8 MIL DTL 83133 Arctic Diesel Fuel DF A conforming to ASTM D 1655 Jet A or Jet ...

Page 54: ...ef Figure 2 4 Cold weather operations Fuels must meet anti icing capability of JP 4 when operating at 4 C 40 F or less Refer to Section VII for additional cold weather fuel information Fuel filter Upon completion of the flight in progress further flight is prohibited until the fuel filter has been serviced following the illumination of the FUEL FILTER caution light Fuel system purging Further flig...

Page 55: ...000 0 20 40 60 80 100 120 140 FUEL TEMPERATURE DEGREES F 0 160 0 10 20 30 40 50 60 70 FUEL TEMPERATURE DEGREES C NOTES 1 USE OF MIL G 5572E FUEL IS LIMITED TO A MAXIMUM OF 6 HOURS OF OPERATION PER ENGINE OVERHAUL PERIOD 2 TO CONSERVATIVELY ESTIMATE THE FUEL TEMPERATURE ASSUME IT TO BE EQUAL TO THE HIGHEST TEMPERATURE THE HELICOPTER HAS BEEN EXPOSED TO DURING THE PRECEDING 24 HOURS F01 007 Figure 2...

Page 56: ...NGE 150 75 150 130 90 125 107 3 F 2 LBS X 100 75 150 50 PSI C 1 30 150 75 75 125 107 C 1 30 3 F 2 LBS X 100 150 DC AMP AMMETER ENG OIL PRESS ENG OIL TEMP ENGINE OIL TEMPERATUIRE FUEL QUANTITY 150 AMPS 66 TO 150 AMPS 0 TO 66 AMPS 50 AND 130 PSI 50 TO 90 PSI 90 TO 130 PSI 107 C 15 TO 30 C 30 TO 107 C FUEL LOW CAUTION 35 POUNDS 140 KNOTS 20 160 20 50 100 150 120 100 140 120 40 40 60 100 80 OIL 0 PRES...

Page 57: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 FAA Approved Revision 5 2 15 F01 002A Figure 2 5 Instrument Markings ...

Page 58: ...0 1 5 2 4 3 80 DUAL TACHOMETER BOTH FACES SHOWN FOR CLARITY G R B Y N2 ROTOR 103 AND 104 103 TO 104 110 ROTOR RPM 400 AND 514 RPM 400 TO 514 RPM 10 12 8 TOT 70 90 100 TORQUE 110 6 4 C X 100 0 2 60 PSI 10 50 20 40 30 749 C 693 TO 749 C 385 TO 693 C 843 C G R B Y 80 3 PSI 70 TO 80 3 PSI 0 TO 70 PSI F01 003 ...

Page 59: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 FAA Approved Revision 5 2 17 Figure 2 6 Instrument Markings Allison 250 C18 Engine ...

Page 60: ... 80 DUAL TACHOMETER G R B Y BOTH FACES SHOWN FOR CLARITY N2 ROTOR 103AND 104 103 TO 104 113 ROTOR RPM 400 AND 523 RPM 400 TO 523 RPM 10 12 8 TOT 6 70 60 90 100 TORQUE 110 4 C X 100 0 2 PSI 10 50 20 40 30 793 c 737 TO 793 C 360 TO 737 C G R B Y 843 C 64 5 PSI 56 TO 64 5 PSI 0 TO 56 PSI F01 004 ...

Page 61: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 FAA Approved Revision 5 2 17 Figure 2 7 Instrument Markings Allison 250 C20 Engine ...

Page 62: ... LESS PRESSURE ALTITUDE C x 1000 OAT 0 1 4 7 10 13 17 20 30 116 73 40 15 130 126 102 58 0 116 86 42 15 127 103 71 30 118 89 56 45 129 107 76 43 VNE KNOTS IAS GROSS WEIGHT MORE THAN 2000 LBS PRESSURE ALTITUDE C x 1000 OAT 0 1 4 7 10 13 30 92 66 15 108 79 54 0 130 128 92 66 43 15 109 80 55 30 94 68 45 45 125 112 83 58 Figure 2 8 VNE Placards Allison 250 C18 ...

Page 63: ...URE ALTITUDE x 1000 C OAT 0 1 4 7 10 13 17 20 30 123 93 52 22 15 108 78 38 0 130 123 93 64 15 109 79 50 30 125 95 66 37 45 112 83 VNE KNOTS IAS GROSS WEIGHT MORE THAN 2200 LBS PRESSURE ALTITUDE x 1000 C OAT 0 1 4 7 10 13 30 91 64 15 107 77 51 0 130 128 91 64 39 15 108 78 52 30 93 66 41 45 125 111 81 55 Figure 2 9 VNE Placards Allison 250 C20 ...

Page 64: ...THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL CAUTION CYCLIC FORCES TO BE TRIMMED TO NEUTRAL DURING STARTUP AND SHUTDOWN NOTE Above placards located on instrument panel 50 POUNDS MAXIMUM LOAD UNIFORMLY DISTRIBUTED NOTE Above placard located inside utility stowage compartment IF MOISTURE VISIBLE AND OAT BELOW 5 C USE ANTI ICE NOTE Above placard located by OAT gauge Fi...

Page 65: ......

Page 66: ... and Caution Indicators 3 2 Figure 3 1 Warning and Caution Indicators 3 2 3 3 Engine Failure 3 3 Complete Power Loss 3 3 Partial Power Loss 3 5 3 4 Air Restart Engine 3 6 3 5 Low Rotor Speed 3 7 3 6 Emergency Landing Procedures 3 7 Water Landing 3 7 3 7 Fire 3 9 Engine Fire on the Ground Engine Fire During Flight 3 10 3 11 Cabin Fire Smoke 3 12 3 8 Engine Fuel Control System Malfunctions 3 14 Fuel...

Page 67: ...ngine Oil Chip Detector Low Engine Oil Pressure 3 16 3 16 Engine Torque 3 16 3 10 Main Rotor and Tail Rotor Transmission Malfunctions 3 17 M R Transmission Oil Pressure 3 17 M R Transmission Oil Temperature 3 17 M R Transmission Chip Detector 3 17 Tail Rotor Transmission Chip Detector Oil Chips 3 18 3 18 Oil Pressure Temperature 3 18 ...

Page 68: ...e 3 20 Cyclic Trim Failure 3 21 3 12 Abnormal Vibrations 3 13 Fuel System Malfunctions 3 23 3 23 Fuel Filter 3 23 Fuel Low 3 24 3 14 Electrical System Malfunctions 3 25 Battery Overtemperature 3 25 Generator Malfunction 3 26 3 15 Other Malfunctions 3 27 Engine Air Particle Separator if installed 3 27 3 16 Emergency Egress 3 28 Figure 3 2 Emergency Exits 3 17 Emergency Equipment 3 28 3 29 ...

Page 69: ...ed 3 1 GENERAL The procedures contained in this section are recommendations to be followed in the event of an emergency or malfunction that may potentially affect the safety of the aircrew passengers aircraft or personnel on the ground These procedures are recommended to minimize danger to the helicopter How ever these procedures should not limit the pilot from taking additional actions if the sit...

Page 70: ...N BATTERY 140F 160F LATE CONFIGURATION CAUTION AND WARNING LIGHTS PARTICLE SEPARATOR BRACKET ASSEMBLY IF INSTALLED ENGINE OUT XMSN OIL PRESS XMSN OIL TEMP GEN OUT ENGINE CHIPS M R XMSN CHIPS T R XMSN CHIPS FUEL LOW FUEL FILTER PRESS TO TEST FILTER CLOGGED SCAV AIR SWITCH 1 2 3 4 5 6 7 8 9 10 RED YELLOW 1 ENGINE OUT 2 TRANSMISSION OIL PRESSURE 3 TRANSMISSION OIL TEMPERATURE 4 GENERATOR OUT 5 ENGINE...

Page 71: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Emergency and Malfunction Procedures FAA Approved Revision 6 3 3 Figure 3 1 Warning and Caution Indicators F01 012 ...

Page 72: ...hen N1 falls below 55 Procedures Engine Failure In Cruise at 420 Feet AGL or Above e Allison C 18 engine Adjust collective pitch according to altitude and airspeed to maintain rotor speed between 400 and 514 RPM e Allison C 20 engine Adjust collective pitch according to altitude and air speed to maintain rotor speed between 400 and 523 RPM e Apply pedal pressure as necessary to control aircraft ya...

Page 73: ...Section V depicts the combinations of airspeeds vs altitudes wherein a successful autorotation landing can be made in the event of an engine failure Flight within the cross hatched regions represent airspeed altitude combinations from which a successful autorotation landing may be difficult to perform Operation within the cross hatched area should be undertaken with caution Procedures e In the eve...

Page 74: ...ing PARTIAL POWER LOSS Indications Under partial power conditions the engine may operate smoothly with reduced power or it may operate erratically with intermittent surges of power Procedures e Turning the start pump ON may smooth out an erratic operating engine and or restore power enabling the pilot to fly to a favorable landing area However do NOT disregard the need to land e If possible fly at...

Page 75: ...tical Procedures e Close twist grip to cutoff position e Press start ignition button immediately NOTE Pressing the starter button actuates the igniter If N1 is 18 percent or above open twist grip immediately to ground idle N1 speeds of 25 to 40 percent are preferred for coolest and fastest restarts Maintain safe autorotational airspeed Conditions When altitude and time permit Procedures e Perform ...

Page 76: ...iated with the following Engine Failure Transient rotor droop during large rapid increases in power Governor failure producing an underspeed Procedures e Respond immediately to the low rotor RPM warning by adjusting collec tive to maintain rotor RPM within limits e Check other Caution Warning indicators and engine instruments to con firm engine trouble and respond in accordance with appropriate pr...

Page 77: ...ed Conditions Power on Procedures e Descend to hovering altitude over water e Open doors and push door handle full down to prevent relatching e Passengers and copilot exit aircraft e Fly a safe distance away from all personnel in the water to avoid injury e Close twistgrip to the cutoff position and perform a hovering autorotation e Allow aircraft to settle in a level attitude while applying full ...

Page 78: ... arcing the smell of burning insulation or the sighting of smoke and or flame are all possible indicators of an on board fire Also the pilot may be notified of an on board fire by personnel outside the aircraft via visual or audio communication methods At unprepared landing sites dried grass or brush may catch fire CAUTION if allowed to contact hot engine exhaust Procedures Cabin Smoke and Fume El...

Page 79: ...commended and should only be considered after all other means to extinguish and control the fire have been tried The pilot s first responsibility is to fly the helicopter and land immediately Once on the ground with passengers and crew evacuated attention can be turned to extinguishing the fire e If a fire extinguisher is discharged in the cabin use only the amount of extinguishing agent necessary...

Page 80: ... TO CLOSE e BATTERY EXT PWR switch OFF e Passengers crew EVACUATE If time and situation permit e Rotor brake if installed APPLY e Secure area HAVE PASSENGERS AND SPECTATORS MOVE A SAFE DISTANCE FROM THE AIR CRAFT e Fire extinguisher USE AS APPROPRIATE ENGINE FIRE DURING FLIGHT Conditions At low altitude AGL Procedures e Land immediately POWER ON APPROACH AND LANDING WITHOUT DELAY e Twistgrip CUTOF...

Page 81: ... descent to the ground If a power off descent is chosen proceed as follows e Collective DOWN TO ESTABLISH AUTOROTATION TO SELECTED AREA e Twistgrip CUTOFF e Fuel shutoff valve PULL TO CLOSE e Radio MAYDAY CALL e Execute autorotational landing MAINTAIN CONTROL e BATTERY EXT PWR switch OFF e Passengers crew EVACUATE CABIN FIRE SMOKE Conditions On ground Procedures e Twistgrip CUTOFF e BATTERY EXT PW...

Page 82: ... NECESSARY e Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND e BATTERY EXT PWR switch OFF e Passengers crew EVACUATE If unable to land immediately and fire source can be identified e Malfunctioning system OFF e Fire extinguisher USE AS NECESSARY e Cabin VENTILATE e Land AS SOON AS POSSIBLE If fire source is unknown e Cabin heat OFF e GEN OFF e All electrical circuits not required for safety of...

Page 83: ...y increasing Possible right yaw Procedures e Increase collective to load the main rotor simultaneously rolling the twist grip toward the ground idle position until control of N2 speed is obtained e Manually control N2 speed 103 104 with the pilots twistgrip e If operating RPM cannot be controlled close twistgrip to CUTOFF and make an autorotational landing CAUTION Immediate pilot action is necessa...

Page 84: ...vel flight or a power on decent make an au torotational landing Conditions Power Turbine Governor Surge Indications N2 fluctuating governor not maintaining pre set speed 103 104 N2 Procedures NOTE Turning the start pump ON may allow the engine to operate smoothly If operation of the engine returns to normal it may be possible to fly to a favorable landing area however do not disregard the need to ...

Page 85: ...ons Yellow OIL CHIPS indicator ON early configuration Conditions Metal contamination of engine main or tail rotor transmission oil Procedures e Land as soon as possible LOW ENGINE OIL PRESSURE Indications Oil pressure decreasing below normal operating range Ref Section II Conditions In flight Procedures e Land as soon as possible e Shut engine down Conditions On ground e Shut engine down ENGINE TO...

Page 86: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Emergency and Malfunction Procedures FAA Approved Revision 6 3 18 Conditions In flight ...

Page 87: ...RE Indications Red XMSN OIL PRESS indicator ON late configuration Conditions Transmission oil pressure low Procedures e Land as soon as possible M R TRANSMISSION OIL TEMPERATURE Indications Red XMSN OIL TEMP indicator ON late configuration Conditions Transmission oil temperature exceeds maximum limit Procedures e Land as soon as possible M R TRANSMISSION CHIP DETECTOR Indications Yellow M R XMSN C...

Page 88: ...n of oil Procedures e Land as soon as possible OIL CHIPS Indications Yellow OIL CHIPS indicator ON early configuration Conditions Metal contamination of engine main or tail rotor transmission oil Procedures e Land as soon as possible OIL PRESSURE TEMPERATURE Indications Yellow XMSN OIL PRESS TEMP indicator ON early configuration Conditions Transmission oil pressure low or transmission oil temperat...

Page 89: ...and power setting Indications Failure is normally indicated by an uncontrollable by pedal yawing to the right Procedures e Reduce power by lowering collective e Adjust airspeed to 50 60 knots e Use left lateral cyclic in combination with collective pitch to limit left sideslip to a reasonable angle e If conditions permit place the twistgrip in the ground idle position once a landing area is select...

Page 90: ...tained hydraulic unit that prevents aft feedback forces in the longitudinal cyclic control system Indications Aft feedback in the cyclic at high airspeed and or during pull ups from high airspeed or higher than normal forces required to move the cyclic longitudinally NOTE If the one way lock has a push rod shaft or check valve seizure in the closed valve position a pull or push of 30 pounds will b...

Page 91: ...copter in continued flight Indications Inoperative trim Conditions The trim motor fails to respond to application of the cyclic trim switch in one or more directions Procedures e Establish a safe flight condition that produces the least cyclic control force Normally straight and level at the last trimmed airspeed e Actuate the trim switch thru all positions in an attempt to restore trim capability...

Page 92: ... NOTE If a forward longitudinal runaway trim failure is experienced it may be possible to reduce cyclic stick forces by maintaining higher airspeeds Cyclic stick forces may be reduced if an aft longitudinal runaway trim failure is experienced by maintaining slower airspeeds Lateral runaway trim forces cannot be reduced by adjusting flight conditions e Utilize left hand and legs as necessary to app...

Page 93: ...dentified and corrected 3 13 FUEL SYSTEM MALFUNCTIONS FUEL FILTER Indications Yellow FUEL FILTER caution indicator on Conditions A predetermined pressure differential across the filter has been reached and an impending bypass condition exists Procedures e Turn on start pump e Continue flight If any unusual engine indications or conditions occur land as soon CAUTION as possible e Turn start pump ON...

Page 94: ...en approximately 35 pounds of fuel remains in fuel tank Procedures e Avoid large steady side slip angles and uncoordinated maneuvers Never use the FUEL LOW light as a working indication of fuel CAUTION quantity e Land as soon as possible WARNING Fuel consumption rates vary with power demand Pilots should land prior to fuel exhaustion Fuel exhaustion will result in engine flameout ...

Page 95: ... switch OFF e Land as soon as possible NOTE No further flights are authorized until battery is inspected and cause of overtemp corrected BATTERY Indications Yellow 140F 160F battery 140 F caution indicator ON Conditions Battery overtemperature at 140 F 60 C Procedures e Battery switch OFF e Battery must remain off line during remainder of flight NOTE The Yellow battery 140 F light will go out afte...

Page 96: ... Check generator GEN circuit breaker IN e Turn the generator GEN switch OFF then ON to reset e If GEN OUT indicator remains ON or comes back ON pull generator cir cuit breaker OUT and insure generator switch is in the ON position for the remainder of the flight NOTE The generator switch must be in the ON position to enable the Engine Out Low Rotor audio warning to function as required e If GEN OUT...

Page 97: ...TALLED Indications Yellow FILTER CLOGGED indicator ON Conditions A predetermined pressure differential has been reached across the engine air inlet Procedures e FILTER BYPASS control handle pull OPEN e SCAV AIR OFF e Service particle separator prior to next flight Ref HMI To prevent compressor erosion avoid operation in a dirty or dusty CAUTION environment with the filter bypass door open ...

Page 98: ...CY EGRESS Pilot compartment doors Pilot doors function as primary and emergency exits Cabin doors Passenger doors function as primary and emergency exits EXIT TO OPEN PILOT COMPARTMENT DOOR LH TYPICAL CAUTION SAFELOCK INNER HANDLE IN POSITION SHOWN BEFORE FLIGHT TO LOCK PILOT PASSENGER COMPARTMENT DOOR EXIT Figure 3 2 Emergency Exits F01 058 ...

Page 99: ...Aid Kit The first aid kit is located on the right side forward edge of the pilot s seat structure The kit is a commercial type containing the items necessary to render lim ited emergency first aid Fire Extinguisher The fire extinguisher is located on the pilot side forward door frame See the paragraph in this section entitled FIRE for recommended use of fire extinguisher ...

Page 100: ......

Page 101: ...Sheet 1 of 2 Figure 4 2 Instrument Panel Sheet 2 of 2 Figure 4 3 Cyclic and Collective Stick Grip 4 9 4 10 4 11 4 2 Engine Pre Start Cockpit Check 4 12 4 3 Engine Start 4 15 4 4 Engine Run Up 4 17 4 5 Before Takeoff 4 19 4 6 Takeoff 4 7 Cruise 4 19 4 21 4 8 Low Speed Maneuvering 4 21 4 9 Practice Autorotation 4 22 4 10 Doors Off Flight 4 23 4 11 Cold Weather Operation 4 24 4 12 Landing Approach 4 ...

Page 102: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 i 4 ii blank 4 17 Normal Engine Restart 4 28 4 18 Noise Impact Reduction Procedures 4 28 ...

Page 103: ......

Page 104: ...evidence of corro sion These are the most common types of damage however checks should not be limited to these items Further checks shall be performed before the next flight if discrepancies are noted to determine if the aircraft is airworthy Flight is prohibited when unrep aired damage exists which makes the aircraft unairworthy Have a thorough understanding of operating limitations Ref Section I...

Page 105: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 2 z m I II 0 II F01 014 Figure 4 1 Pilot s Preflight Guide ...

Page 106: ...rcraft tiedowns and covers REMOVED e Aircraft attitude for weak or damaged dampers CHECK e Canopy e e Condition and cleanliness CHECK e e OAT thermometer sun shield CHECK e Fresh air vent NO OBSTRUCTIONS e Pitot tube NO OBSTRUCTIONS e Anti torque pedals e e Condition and security of quick release pins both sides with dual controls CHECK e Landing light CHECK e Antennas CHECK e Lower access panels ...

Page 107: ...interior e e Seats seat belts and shoulder harness CHECK e e Co pilot controls if installed CHECK e e First aid kit CHECK e e Airworthiness and Registration certificates CHECK e Right front door for condition and latching CHECK e Right cabin interior e e Forward landing gear damper CHECK e e Seats seat belts and shoulder harness CHECK e e Loose equipment or cargo SECURED NOTE With passengers in ca...

Page 108: ...now clear engine inlet CAUTION area and surrounding skin areas of all accumulated snow and ice Open plenum chamber door and inspect the inlet screen and particle separator if installed for ice and snow blockage e Oil cooler air inlet CHECK e All inspection panels and cabin doors SECURED e Fuel level cap security CHECK e Engine oil level cap security CHECK NOTE Engine oil level should be checked wi...

Page 109: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 6 movement CHECK ...

Page 110: ...eparation or a vibration is noted Evidence of light swelling pock marks and crumbs are surface conditions and are not indications of bearing failure e e Apply teetering force by hand to tail rotor blades stop to stop Check for fork to bearing bond failure Failure is indicated by any motion between outer bearing cage and fork bearing turns in fork e e Teeter blades stop to stop Observe four radial ...

Page 111: ...Normal Procedures FAA Approved Revision 5 4 7 NOTE If tail rotor blade tip moves in excess of 3 4 inch 1 9 cm without coincidental movement of the main rotor blades inspect tail rotor drive shaft couplings in accordance with the Handbook of Maintenance Instructions ...

Page 112: ...lation and evidence of hard landing CHECK e Engine oil air and fuel lines CHECK e Engine electrical connections CHECK e Fuel control N2 governor and associated linkages CHECK e Scavenge oil filter bypass indicator if installed CHECK e Exhaust ducts CHECK e Engine compartment doors for condition and security CHECK FUSELAGE LH SIDE ffi e Skid strut fairings strut cuff CHECK e Position light skid or ...

Page 113: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 9 e Anti collision light CHECK ...

Page 114: ...CHECK e Fire extinguisher and first aid kit CHECK e Loose equipment or cargo CHECK NOTE Refer to Paragraph DOORS OFF FLIGHT if planning flight with doors removed e Seats seat belts and shoulder harness CHECK e Interior and exterior lights all switches OFF after check CHECK PREFLIGHT CHECKS Perform these checks prior to subsequent flights of the same day e Fluid levels CHECK e Engine compartment fl...

Page 115: ...ARNING HORN CAUTION AND WARNING LIGHTS AIRSPEED INDICATOR BATTERY 140F 160F OIL CHIPS MAGNETIC COMPASS SCAVENGE AIR IF INSTALLED N2 AND NR ROTOR TACHOMETER INDICATOR ALTIMETER BLANK PLATES 5 PLACES TORQUE GAGE TURBINE OUTLET TEMPERATURE TOT INDICATOR START PUMP LIGHT N1 TACHOMETER IN DICATOR FAIRING AND HOOD INSTRUMENT CLUSTER 4 PACK F01 013 1 Figure 4 2 Instrument Panel Sheet 1 of 2 ...

Page 116: ...UTION AND WARNING LIGHTS ENGINE OUT AUDIBLE WARNING HORN BATTERY 140F 160F CLOCK CAUTION AND WARNING LIGHTS AIRSPEED INDICATOR SCAVENGE AIR IF INSTALLED ALTIMETER N2 AND NR ROTOR TACHOME TER INDICATOR TORQUE GAGE TURBINE OUTLET TEMPERATURE TOT INDICATOR N1 TACHOMETER INDICATOR INSTRUMENT CLUSTER 3 PACK ENGINE OIL PRESSURE INDICATOR F01 013 2 ...

Page 117: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 1 1 Figure 4 2 Instrument Panel Sheet 2 of 2 ...

Page 118: ...HROTTLE TWIST GRIP FRICTION NUT COLLECTIVE STICK FRIC TION NUT LANDING LIGHT SWITCH GOVERNOR INCREASE DE CREASE SWITCH PILOT S COLLECTIVE STICK SWITCH HOUSING COPILOT S TWISTGRIP COPILOT S COLLECTIVE STICK OPTIONAL DWN CARGO HOOK RE LEASE R ICS COMM L TRIGGER CYCLIC TRIM SWITCH UP START BUTTON PILOT S COL LECTIVE F01 012 Figure 4 3 Cyclic and Collective Stick Grip ...

Page 119: ... Operation of shoulder harness inertia lock CHECK e Cyclic collective frictions off and pedals CHECK FULL TRAVEL e Cyclic stick NEUTRAL FRICTION ON NOTE Cyclic stick longitudinal neutral position is about 35 percent 1 3 travel from full aft lateral position may be determined by centering the friction control knob in the guide link e Tail rotor pedals CENTERED e Collective stick FULL DOWN FRICTION ...

Page 120: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 1 4 e Static position of all instruments CHECK ...

Page 121: ...ad e e Lights AS REQUIRED e e Ignition key ON e ENGINE OUT warning system check GEN SWITCH ON THEN OFF NOTE Proper engine out warning system operation is indicated by flashing indicator light on the caution and warning light panel and audible warning in headsets if installed and external horn mounted on the instrument panel Audio warning system will be inoperative if generator GEN switch is set to...

Page 122: ...e PNL LT circuit breaker e e Caution light dimming lights on some later models may be dimmed by pressing the legend face of the indicator Pressing the indicator a second time restores the light to bright e Twistgrip to FULL OPEN return to GROUND IDLE STOP then to CUTOFF position e Cyclic trim control check CHECK CHECK e e Cyclic friction OFF e e Momentarily motor cyclic trim control forward left r...

Page 123: ...n II Minimum N1 Speed Starting Recommendations Placard NOTE The 250 C20 Series engine has two qualified control systems They are The Bendix system which uses an automatic start mode and the CECO system which uses a modulated start mode The 250 C18 Series engine uses only the automatic start mode Automatic Start Mode Bendix system Rotate twistgrip to ground idle for ignition when N1 indicates 12 to...

Page 124: ...rt start procedures e e Close twistgrip to the cutoff position e e Use starter to continue motoring engine for at least ten seconds or until TOT decreases below 150 C e Start ignition button release at 58 to 60 percent N1 RELEASE e Engine oil pressure 50 to 130 psi CHECK NOTE During cold weather operation 150 psi oil pressure is allowable following an engine start Remain at ground idle RPM until n...

Page 125: ...bine N2 speed limits speed avoid range e Electrical power SELECT e e External start Set BATTERY EXT PWR switch to BATTERY disconnect external power source e Set generator GEN to ON GEN OUT caution light out ammeter will show charge CHECK OPERATE AND CHECK e Cyclic friction RELEASE AND SET AS DESIRED e Avionics as required ON AND CHECK e Twistgrip FULL OPEN Check for unusual aircraft vibration or n...

Page 126: ...to reignition if installed ON at 98 1 percent e Engine bleed air device checks e e SCAV AIR switch if installed observe slight rise in TOT about 5 C e e Engine ANTI ICE ON Observe TOT increase 10 15 C e e CABIN HEAT if installed ON observe 20 30 C increase in TOT CHECK ON CHECK CHECK e e CABIN HEAT OFF NOTE TOT DECREASE e e ANTI ICE switch OFF NOTE TOT DECREASE e e SCAV AIR if installed PILOT S DI...

Page 127: ...NING When removing collective friction be alert for abnormal collective loads that would cause the collective to raise by itself e Cyclic response check e e With collective pitch full down gently move cyclic stick and observe rotor tip for correct movement and track CHECK e All instruments in the green CHECK e Position and anti collision lights AS REQUIRED e Pitot heat if installed AS REQUIRED e S...

Page 128: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Normal Procedures FAA Approved Revision 5 4 20 Reduction Procedures Determine that hover area and takeoff path are clear ...

Page 129: ... has been identified and corrected Follow recommended takeoff profile shown in Height Velocity CAUTION Diagram Refer to Section V NOTE Momentary fluctuation in indicated airspeed may occur during acceleration and climbout This fluctuation is characterized by a rapid rise in indicated airspeed to approximately 40 knots followed by a drop back to 30 knots and then normal increase as determined by th...

Page 130: ...roper trimming procedures described for climbout Above 50 knots and 50 foot altitude above terrain select N2 between 103 and 104 percent for best comfort level Use engine anti icing when OAT is below 5 C 41 F and visible moisture conditions prevail 4 8 LOW SPEED MANEUVERING Avoid maneuvers that exceed thrust capability of the tail rotor NOTE Conditions where thrust limits may be approached are Hig...

Page 131: ...ht is being conducted at high gross weight or high density altitude To reduce rate of descent or to extend gliding distance operate at minimum rotor rpm Restore rotor rpm by lowering collective prior to flareout If a power recovery is desired lower collective to full down rotate the twist grip to the full open position verify that N2 is between 103 and 104 percent and that full engine power is ava...

Page 132: ...the following WARNING Any object that is not properly secured may exit the aircraft during flight 1 Items ie first aid kit seat cushions secured with velcro should not be considered properly secured 2 Secure or stow in the baggage compartment all loose equipment 3 Secure or remove unoccupied seat cushions 4 Secure folding tables 369HE only For HE HS aircraft with serial numbers 0101E thru 0215E an...

Page 133: ...ed that the 369H90127 Winterization Kit be installed Helicopters 0333S and 0216E and subs have the kit installed as standard equipment 4 12 LANDING APPROACH Set N2 to 104 percent Set SCAV AIR if installed as required 4 13 RUNNING LANDING Maximum recommended ground contact speed is 30 knots for smooth hard sur face Avoid rapid lowering of the collective after ground contact Avoid the use of aft cyc...

Page 134: ...ON ON e Cyclic stick neutral position approximately 1 3 from full aft TRIM TO NEUTRAL APPLY FRICTION e All unnecessary bleed air and electrical equipment OFF e Pedals maintain until rotor has stopped CENTERED e Twistgrip from GROUND IDLE to CUTOFF position SET NOTE Immediately after closing twistgrip to the CUTOFF position a dual tachometer needle split should occur with NR lagging behind N2 If no...

Page 135: ...otor e Generator switch OFF e NAV COM switches OFF e All other switches OFF Care should be taken while applying the rotor brake if the helicopter CAUTION is parked on a slippery or icy surface The tail rotor control is minimized at less than normal operating RPM when the engine is not driving the rotor system Full control of the helicopter during these conditions may be limited Damage to the rotor...

Page 136: ...t exactly 104 percent BEEP as required SET e Pilot s twistgrip SNAP TO IDLE Begin time check with stop watch Stop time as N1 passes through 65 percent Observe elapsed time Minimum allowable lapsed time is 2 seconds NOTE Practice or retakes may be required before proficiency can be obtained in deceleration timing If deceleration time is less than two seconds make two more checks to confirm time If ...

Page 137: ... It is imperative that every pilot subject the public to the least possible noise while flying the helicopter Takeoff Takeoff using maximum takeoff power at the speed for best rate of climb Proceed away from noise sensitive areas If takeoff must be made over noise sensitive area distance altitude is the best form of noise suppression Cruise Maintain 1000 feet minimum altitude where possible Mainta...

Page 138: ...ram 5 8 Figure 5 4 Height Velocity Diagram 5 9 Figure 5 5 Gross Weight Limits for Height Velocity Diagram 5 10 5 6 Hover Ceiling vs Temperature IGE 5 11 Figure 5 6 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Takeoff Power Allison 250 C18 5 13 Figure 5 7 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Aluminum Tail Rotor Takeoff Power Sheet 1 ...

Page 139: ...d Clearance Extended Landing Gear Aluminum Tail Rotor Takeoff Power Allison 250 C18 Figure 5 10 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Aluminum Tail Rotor Takeoff Power Allison 250 C18 Figure 5 11 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Takeoff Power Allison 250 C18 5 15 5 16 5 17 5 18 5 19 ...

Page 140: ...20 5 23 Figure 5 16 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended Landing Gear Take off Power Allison 250 C20 5 24 Figure 5 17 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended Landing Gear Tail Rotor Blade Abrasion Strips Installed Takeoff Power Allison 250 C20 5 25 Figure 5 18 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Takeoff Power ...

Page 141: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Performance Data FAA Approved Revision 5 5 i Allison 250 C20 5 34 ...

Page 142: ...equipped with the Allison 250 C18 or 250 C20 engines When any data is affected by model designation or engine configuration that information will be so noted Be sure to select the appropriate performance data for model type engine and optional equipment installed Figure numbers marked with an asterisk indicate data pertinent to an installed optional equipment item This section contains helicopter ...

Page 143: ...psi 5 2 AIRSPEED CALIBRATION CURVE Description This chart shows the difference between indicated and calibrated airspeeds Indicated airspeed IAS corrected for position and instrument error equals calibrated airspeed CAS Use of Chart Use the chart as illustrated by the example To determine calibrated air speed the pilot must know the indicated air speed Example WANTED Calibrated airspeed KNOWN Indi...

Page 144: ...0 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CALIBRATED AIRSPEED KTS 160 150 140 130 120 110 100 90 80 70 60 50 40 PITOT SYSTEM 369H4226 STATIC SYSTEM 369H6610 501 30 30 40 50 60 70 80 90 100 110 120 130 140 150 INDICATED AIRSPEED KTS F01 057 Figure 5 1 Airspeed Calibration Curve ...

Page 145: ...e up to known pressure altitude line move to left and note densi ty altitude NOTE Pressure altitude is found by setting 29 92 1013 mb in kolsman window altimeter error To determine true airspeed convert indicated airspeed IAS to calibrated airspeed CAS utilizing the Airspeed Calibration Curve Ref Figure 5 1 Read value on right of chart opposite known density altitude Multiply CAS by this value to ...

Page 146: ...ORCRAFT FLIGHT MANUAL DENSITY ALTITUDE FEET 20000 1 36 18000 1 34 1 32 16000 1 30 1 28 1 26 14000 1 24 1 22 12000 1 20 10000 1 18 1 16 8000 1 14 1 12 6000 1 10 1 08 4000 1 06 2000 1 04 1 02 0 1 00 2000 30 20 10 0 10 20 30 40 TEMPERATURE C 50 60 0 98 20 10 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 ...

Page 147: ... Allison 250 C18 FAA Approved Revision 5 5 6 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL EMPERATURE F F01 055 Figure 5 2 Density Altitude Chart ...

Page 148: ...irspeed to use for the best rate of climb at any given density altitude Use of Chart Use the chart as illustrated by the example below Example Wanted Best rate of climb Known Density altitude 9 000 feet Gross Weight 2100 pounds Method Enter the left side of chart at the known density altitude of 9 000 feet Move to the right along line and read 60 knots indi cated airspeed IAS as the best rate of c...

Page 149: ...ce Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL DENSITY ALTITUDE FEET 20 000 18 000 16 000 14 000 2000 lb 2200 lb 2550 lb 12 000 10 000 8 000 6 000 4 000 2 000 0 0 10 20 30 40 50 60 70 INDICATED AIRSPEED KNOTS F01 015 Figure 5 3 Speed for Best Rate of Climb ...

Page 150: ...hin the cross hatched area is not prohibited but should be undertaken only with extreme caution The recommended takeoff profile line shows the airspeed altitude combina tions recommended for takeoff sequence The unmarked region represents the area in which safe autorotational land ings may be performed with average pilot skill and reaction time Gross Weight Limits for Height Velocity Diagram Descr...

Page 151: ... HM ROTORCRAFT FLIGHT MANUAL ALTITUDE AGL METERS ALTITUDE AGL FT 500 400 300 SMOOTH HARD SURFACE WIND CALM AVOID OPERATION IN CROSSHATCHED AREAS 150 125 100 RECOMMENDED TAKEOFF PROFILE 75 200 50 100 25 0 0 0 20 40 60 80 100 120 140 INDICATED AIRSPEED KNOTS F01 018 Figure 5 4 Height Velocity Diagram ...

Page 152: ...a MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL DENSITY ALTITUDE METERS DENSITY ALTITUDE FEET 7000 2000 6000 5000 4000 3000 2000 1000 0 2000 1500 1000 500 0 2100 2200 2300 2400 2500 2600 GROSS WEIGHT LB F01 023 Figure 5 5 Gross Weight Limits for Height Velocity Diagram ...

Page 153: ...off power at 104 N2 2 Cabin heat and engine anti ice OFF 3 Electrical load of 10 amps If cabin heat and or anti ice are used reduce weight capability LBS as per the applicable chart If the engine air particle separator is installed hover performance is af fected Reduce takeoff gross weight by Allison 250 C18 33 pounds with particle separator 11 pounds with engine inlet screen 369H8086 installed Al...

Page 154: ...tside air temperature Example Helicopter configuration Short landing gear Standard engine air inlet Engine bleed air devices OFF 250C 18 engine Wanted Maximum gross weight for hover at 3 0 feet skid height at takeoff power Known Gross weight 2190 Ambient Temperature 25 C Method Select the appropriate chart Figure 5 6 for this example Enter the chart at 25 C on the ambient temperature scale and mov...

Page 155: ...2 125 105 ICE 204 160 130 405 295 255 20 000 18 000 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 20000 90 110 210 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5 7 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 5 000 4 000 3 000 2 000 1 000 GRO...

Page 156: ...formance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C18 FAA Approved Revision 5 5 14 Figure 5 6 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Takeoff Power F01 024 ...

Page 157: ...NE ANTI ICE OFF ELECTRIC LOAD 15 AMPERE APPLICABLE TO STAN DARD ER NE GD IN U E CA EIR HO IN V L E E R T W 25 E0 IG C H1 T8C E A N P G AIB NIE LITY 1 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT ...

Page 158: ...a MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C18 FAA Approved Revision 5 5 16 Figure 5 7 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Aluminum Tail Rotor Takeoff Power Sheet 1 of 2 ...

Page 159: ...094 EN ALT FT HEAT ICE GINE AIR INLET SCREEN 250 C18 ENGINE SEA LEVEL REDUCE HOVER WEIGHT CAPABILITY 1 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON TO 10000 15000 125 105 155 130 290 240 20 000 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 20000 85 105 195 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 ...

Page 160: ...CRAFT FLIGHT MANUAL Allison 250 C18 FAA Approved Revision 5 5 18 0 0 40 30 20 10 0 10 20 30 40 AMBIENT TEMPERATURE DEGREES F01 026 Figure 5 7 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Aluminum Tail Rotor Takeoff Power Sheet 2 of 2 ...

Page 161: ...0 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED FEET SEA LEVEL TO 10 000 15 000 20 000 HEAT 125 105 85 ICE 155 130 105 290 240 195 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5 7 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 5 000 4 000 3 000 2 000 1 000 GROSS WEIGHTS ABOVE 2550 LB MUS...

Page 162: ...FAA Approved Revision 5 5 20 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL F01 031A Figure 5 8 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended Landing Gear Takeoff Power ...

Page 163: ... 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON ALT FT SEA LEVEL TO 1000 15000 HEAT 125 105 ICE 155 130 290 240 20 000 18 000 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 20000 85 105 195 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5 7...

Page 164: ...proved Revision 5 5 22 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Figure 5 9 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended Landing Gear Aluminum Tail Rotor Takeoff Power ...

Page 165: ...ITY 1 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 ALT FT SEA LEVEL TO 1000 15000 HEAT 125 105 ICE 155 130 290 240 20 000 18 000 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 20000 85 105 195 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2...

Page 166: ...Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL NOTE 5 FOOT SKID CLEARANCE WITH EXTENDED LANDING GEAR INSTALLED F01 028 Figure 5 10 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Aluminum Tail Rotor Takeoff Power ...

Page 167: ...NGE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5 7 16 000 14 000 12 000 10 000 8 000 5 000 4 000 3 000 6 000 4 000 2 000 WEIGHT GREATER THAN 2550 LB MUST BE EXTERNAL AND JETTISONABLE 2 000 1 000...

Page 168: ... C18 FAA Approved Revision 5 5 26 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Figure 5 11 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Takeoff Power ...

Page 169: ...ITY 1 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5 7 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 5 000 4 000 3 000 2 000 1 000 0 40 30...

Page 170: ...ved Revision 5 5 28 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Figure 5 12 Hover Ceiling vs Temperature IGE 2 Foot Skid Clearance Extended Landing Gear Utility Floats Installed Takeoff Power ...

Page 171: ...RE APPLICABLE TO 369H8094 ENGINE AIR INLET SCREEN 250 C18 ENGINE REDUCE HOVER WEIGHT CAPABILITY 1 33 LB WITH PARTICLE SEPARATOR 2 33 LB WITH SCAVENGE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OROAT CINCR E5 ASE1 5 35 IN 6 000 ELECT W RT ICAL LOA 2D 5...

Page 172: ...ision 5 5 30 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Figure 5 13 Hover Ceiling vs Temperature IGE 2 Foot Skid Clearance Extended Landing Gear Aluminum Tail Rotor and Utility Floats Takeoff Power ...

Page 173: ...ED FEET SEA LEVEL TO HEAT ICE BOTH 20 000 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 8 000 12 000 16 000 20 000 162 132 116 98 175 144 123 108 348 288 250 217 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION E IN ELE...

Page 174: ...ormance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C20 FAA Approved Revision 5 5 23 F01 035A Figure 5 14 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Takeoff Power ...

Page 175: ...BRASION TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED FEET SEA LEVEL TO 8 000 12 000 16 000 20 000 HEAT 162 132 116 98 ICE 175 144 123 108 348 288 250 217 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCR...

Page 176: ...00 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C20 FAA Approved Revision 5 5 25 Figure 5 15 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Short Landing Gear Tail Rotor Blade Abrasion Strips Installed Takeoff Power ...

Page 177: ...APABILITY 1 33 LB WITH SCAVENGE AIR ON 2 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD 6 000 18 000 ...

Page 178: ...erformance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C20 FAA Approved Revision 5 5 27 Figure 5 16 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended Landing Gear Take off Power ...

Page 179: ... ON 2 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED ALT FT SEA LEVEL TO HEAT ICE 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE 12 000 132 144 288 20 000 OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 116 98 123 108 250 217 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPE...

Page 180: ...M ROTORCRAFT FLIGHT MANUAL Landing Gear Tail Rotor Blade Abrasion Strips Installed Takeoff Power Allison 250 C20 FAA Approved Revision 5 5 26 AMBIENT TEMPERATURE DEGREES C F01 038 Figure 5 17 Hover Ceiling vs Temperature IGE 3 Foot Skid Clearance Extended ...

Page 181: ...AT ICE 2 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY 8 000 162 175 348 12 000 132 144 288 20 000 OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 116 98 123 108 250 217 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUC...

Page 182: ...nding Gear Tail Rotor Blade Abrasion Strips Installed Takeoff Power Allison 250 C20 FAA Approved Revision 5 5 28 NOTE 5 FOOT SKID CLEARANCE WITH EXTENDED LANDING GEAR INSTALLED F01 039 Figure 5 18 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short Landing Gear Takeoff Power ...

Page 183: ...0 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED ALT FT SEA LEVEL TO HEAT ICE 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY 8 000 162 175 348 12 000 132 144 288 20 000 OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 116 98 123 108 250 217 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE ...

Page 184: ...ding Gear Tail Rotor Blade Abrasion Strips Installed Takeoff Power Allison 250 C20 FAA Approved Revision 5 5 30 AMBIENT TEMPERATURE DEGREES NOTE 5 FOOT SKID CLEARANCE WITH EXTENDED LANDING GEAR INSTALLED F01 040A Figure 5 19 Hover Ceiling vs Temperature IGE 6 Foot Skid Clearance Short ...

Page 185: ... SCAVENGE AIR ON 2 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER ALT FT SEA LEVEL TO HEAT ICE AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER 12 000 132 144 288 20 000 INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 116 98 123 108 250 217 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUD...

Page 186: ...ail Rotor Blade Abrasion Strips Installed Takeoff Power Allison 250 C20 FAA Approved Revision 5 5 32 40 30 20 10 0 10 20 30 40 AMBIENT TEMPERATURE DEGREES C 50 F01 041 Figure 5 20 Hover Ceiling vs Temperature IGE 2 Foot Skid Clearance Extended Landing Gear Utility Floats Installed Takeoff Power ...

Page 187: ...he engine is producing specification power or if engine power deterioration has occurred NOTE Power check data taken at regular intervals should be plotted to monitor trends in engine condition See Allison 250 C18 Series Operation and Maintenance Manual for additional information on trend analysis The power check chart is based on the following conditions 103 percent N2 Cabin heat and engine anti ...

Page 188: ...ve left and read specification TOT of 610 C Compare the specification TOT of 610 C with the TOT observed during flight 600 C for this example The TOT that was observed is lower than the specification TOT If the TOT observed had been higher than the specification TOT read from the chart some power deterioration will have occurred and the performance data given in this manual may not be obtained Whe...

Page 189: ...E HS HM ROTORCRAFT FLIGHT MANUAL 400 500 600 TURBINE OUTLET TEMPERATURE DEGREES C 700 TOT LIMIT 800 0 20 TORQUE PSI 40 60 N2 103 CABIN HEAT ANTI ICE OFF 30 AMPERES ELECTRICAL LOAD 80 TORQUE LIMIT 100 100 150 200 250 300 350 SHAFT HORSEPOWER F01 049 Figure 5 21 Power Check Chart ...

Page 190: ...FAA Approved Revision 5 5 32 CSP HE HS 1 Performance Data MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL Allison 250 C18 ...

Page 191: ...ted to monitor trends in engine condition See Allison 250 C20 Series Operation and Maintenance Manual for additional information on trend analysis The power check chart is based on the following conditions 103 percent N2 Cabin heat and engine anti ice OFF Particle separator SCAV AIR OFF 30 amperes electrical load WARNING Do not exceed engine aircraft limits Accessories required for safe flight sho...

Page 192: ...bserved is low er than the specification TOT If the TOT observed had been higher than the specification TOT read from the chart some power deteriora tion will have occurred and the performance data given in this manu al may not be obtained When trend check procedures indicate engine power deterioration re fer to the Allison Operation and maintenance Manual for corrective action NOTE Data obtained ...

Page 193: ...RAFT FLIGHT MANUAL SHAFT HORSEPOWER 400 350 300 250 200 150 100 100 N2 103 CABIN HEAT ANTI ICE OFF 30 AMPERES ELECTRICAL LOAD 80 TORQUE LIMIT 60 TORQUE PSI 40 20 0 850 TOT LIMIT 800 750 700 650 600 550 TURBINE OUTLET TEMPERATURE DEGREES C F01 056 Figure 5 22 Power Check Chart Allison 250 C20 ...

Page 194: ...igure 6 6 Sample Basic Weight and Balance Record Figure 6 7 Fuel Station JET A at 6 8 Pounds per Gallon Sheet 1 of 2 Figure 6 7 Fuel Station JET B at 6 5 Pounds per Gallon Sheet 2 of 2 6 5 6 6 6 7 6 8 6 9 6 10 6 11 6 2 Weight and Balance Criteria 6 12 6 3 Equipment Removal or Installation 6 12 6 4 Weight and Balance Determination Passenger Configuration 6 12 Example I Longitudinal CG Calculation P...

Page 195: ...MD 500 ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Revision 6 6 i 6 ii blank 6 8 Internal Loading of Cargo 6 20 Table 6 4 Cargo Weight vs Loop Restraint 6 20 Figure 6 8 Cargo Restraint 6 21 ...

Page 196: ......

Page 197: ...line rotor hub centerline is located at Station 100 See Figure 6 2 and Figure 6 3 Cargo Deck Capacity 950 or 1300 pounds not to exceed 115 pounds per square foot Ref Sec tion II Utility Stowage Compartment Limited to 50 pounds Center of Gravity Limits Lateral is right of centerline lateral is left of centerline when seated in the crew compartment looking forward Table 6 1 Center of Gravity Limits ...

Page 198: ...6 2 LONGITUDINAL TRAVEL INCHES FUSELAGE STATIONS FORWARD 97 99 104 105 106 AIRCRAFT GROSS WEIGHTS 2401 TO 2550 LB 1089 TO 1157 KG 2201 TO 2400 LB 998 TO 1089 KG 2001 TO 2200 LB 907 TO 998 KG 2000LB OR LESS 907 KG OR LESS 3 1 0 3 4 5 LATERAL TRAVEL INCHES F01 006 Figure 6 1 Center of Gravity Envelope ...

Page 199: ...ROTOR C STAL 100 0 STA 124 0 CARGO COMPARTMENT STA 28 0 STA 174 0 18 1 2 6 12 1 13 0 CG OF FWD PASSENGER 12 1 CG OF AFT PASSENGERS CG OF PILOT THREE PLACE COCKPIT STANDARD STA 71 5 STA 73 5 STA 105 0 STA 78 50 CG OF COPILOT PASSENGER STA 28 0 13 0 13 0 TWO PLACE COCKPIT OPTIONAL HE HS CG OF PILOT STA 73 5 F01 060 Figure 6 2 Balance Diagram Sheet 1 of 2 ...

Page 200: ...01 THRU 0100 ONLY 20 40 60 80 100 120 140 160 180 200 210 240 260 280 300 SLING POINT LEVELING PLUMB STA 92 6 OIL TANK RH SIDE FIREWALL 3 JIG POINT AFT JACKING POINT STA 197 2 BATTERY STA 78 5 REFERENCE STA 124 0 JIG POINT STA 174 0 BHD ENGINE SECTION FUEL CELL COMPARTMENT STA 282 0 DATUM FWD JACKING POINT STA 96 9 f01 061 Figure 6 2 Balance Diagram Sheet 2 of 2 ...

Page 201: ...A 124 00 I STA 137 50 I STA 146 62 STA 155 75 I STA 164 87 STA 174 00 STA 185 89 CANT STA 197 78 I I WL 49 37 I I I I STA 0 00 I I I I I I I STA STA STA STA STA STA STA 44 65 56 85 84 79 96 42 108 04 119 67 137 50 STA 300 00 WL 104 22 WL 55 34 H CANT STA 197 78 I CANT STA 209 78 CANT STA 219 96 CANT STA 242 14 CANT STA 264 32 STA 279 20 UPPER VERT STABILIZER ATTACHMENT HOLES 101 062 Figure 6 3 Sta...

Page 202: ...MENT INCH LBS LATERAL MOMENT INCH LBS LEFT MAIN 96 9 25 6 RIGHT MAIN 96 9 25 6 TAIL 197 2 0 0 TOTAL UNADJUSTED NET WEIGHT TOTAL WEIGHT OF SURPLUS EQUIPMENT SEE TABLE 1 TOTAL WEIGHT OF MISSING EQUIPMENT SEE TABLE TOTAL BASIC WEIGHT a sv A REFER TO THE OWNER S MANUAL FOR C G LIMITS APPLI ROSS WEIGHT RANGE FUEL OIL ABOARD AT TIME OF WEIGHING FUEL ENGINE OIL MAIN GEAR BOX TAIL GEAR BOX EMPTY D D D D F...

Page 203: ...ODEL SERIAL N REGISTRATIDN NO DATE EXAMPLES OF FORWARD AFT AND LAT ERAL LOADING EXAMPLE 1 FORWARD APPROVED FWO C G LIMIT FOR EXAMPlE 1 GROSS WEIGHT_ _INCHES EXAMPLE 2 AFT WEIGHT LONG ARM iiNl LONG MOMENT liN LBl BASIC WEIGHT PILOT 73 5 GROSS WEIGHT ZERO FUEL AFT C G APPROVED AFT C G LIMIT FOR EXAMPLE 2 GROSS WEIGHT_ _INCHES EXAMPLE J LATERIAL APPROVED LATERAL C G FOR EXAMPLE 3 GROSS WEIGHT_ _INCHE...

Page 204: ...ATE _ WEIGHT ARM INCHES MOMENT INILBS EQUIPMENT ITEM LBS LONG LATR LONGLATR SURPLUS EllUIPMENT TOTAL 1 3 96 9 126 l JACK PADS 2 l 3 96 9 126 1 IO _ Vd i _A v V OL 77 0 f MISSING EllUIPMENT TOTAL 15 9 97 4 1549 ONE QT ENGINE OIL 2 1 133 4 UNUSABLE Fl EL 12 0 93 0 280 1116 FLIGHT MANl AL 1 8 85 0 153 1 OH 1 1107 RfV 4 R 1J Page of McDonnell Douglas Helicopter Company F01 064 ...

Page 205: ...MD500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Weight and Balance Data Revision 6 6 9 Figure 6 5 Sample Surplus and Missing Items ...

Page 206: ...D BALANCE AIRCRAFT MODEL SERIAL NUMBER REGISTRATION NUMBER PAGE 4 OF 4 369E WEIGHT CHANGE RUNNING TOTAL BASIC AIRCRAFT ADDED REMOVED ITEM NO DESCRIPTION OF ARTICLE OR MODIFICATION DATE LONG ARM LONG ARM LONG ARM MOMENT IN LB MOMENT IN LB MOMENT IN LB WEIGH T WEIGH T WEIGH T IN OUT 1273 108 36 137840 ACTUAL BASIC WEIGHT DELIVERY Hughes Helicopters Inc F01 065 Figure 6 6 Sample Basic Weight and Bala...

Page 207: ...lb moment FUEL WEIGHT POUNDS 460 440 NOTES FUEL WT AND CG CURVE USING JET A 65 420 400 60 380 55 360 340 50 320 300 45 280 40 260 240 35 220 30 200 180 25 160 20 140 120 15 100 10 80 60 5 40 0 20 0 1 WEIGHTS AND MOMENTS BASED ON JET A FUEL ASTM D 1655 AT 6 8 POUNDS PER GALLON 2 TOTAL WEIGHT OF FUEL IS DEPENDENT UPON THE SPECIFIC GRAVITY AND TEMPERATURE VARIATION SHOULD BE ANTICIPATED IN GAUGE READ...

Page 208: ...in lb moment FUEL WEIGHT POUNDS 460 440 NOTES FUEL WT AND CG CURVE USING JET B 65 420 400 60 380 55 360 340 50 320 300 45 280 40 260 240 35 220 30 200 180 25 160 20 140 120 15 100 10 80 60 5 40 20 0 0 1 WEIGHTS AND MOMENTS BASED ON JET B ASTM D 1655 AT 6 5 POUNDS PER GALLON 2 TOTAL WEIGHT OF FUEL IS DEPENDENT UPON THE SPECIFIC GRAVITY AND TEMPERATURE VARIATION SHOULD BE ANTICIPATED IN GAUGE READIN...

Page 209: ...the gross weight and longitudinal center of gravity fore and aft for a given flight are within limits proceed as follows Obtain aircraft delivered weight and moment from the Weight and Balance Record inserted in this section Determine weights and moments of useful load items Add above items Ref Example I Determine corresponding center of gravity for gross weight by dividing total moment by gross w...

Page 210: ...17 850 1 100 4 400 1 280 170 170 170 170 170 20 40 138 905 12 500 12 500 12 155 17 850 17 850 1 100 4 400 1 Zero Fuel Weight Add Fuel 2 048 350 204 320 34 000 2 190 350 217 260 34 000 2 Gross Weight 2 398 238 320 2 540 251 260 Calculation of Longitudinal CG CG Zero Fuel Weight 369HE Moment at Zero Fuel Weight 204 320 99 8 in Zero Fuel Weight 2 048 369HS Moment at Zero Fuel Weight 217 260 99 2 in C...

Page 211: ...he approved CG limits To determine the gross weight and center of gravity for a given flight are with in limits proceed as follows Establish the weight of the cargo load Determine the location of the cargo longitudinal CG by measuring the dis tance to the cargo from the jacking point located on the side of the fuselage station 96 9 Cargo CG 96 93 measured distance inches ie if aft of mark if forwa...

Page 212: ...5 12 500 12 500 50 800 1 Zero Fuel Weight Add Fuel 1 978 400 201 765 39 100 2 120 400 214 705 39 100 2 Gross Weight 2 378 240 865 2 520 253 805 Calculation of Longitudinal CG CG Zero Fuel Weight 369HE Moment at Zero Fuel Weight 201 765 102 1 in Zero Fuel Weight 1 978 369HS Moment at Zero Fuel Weight 214 705 101 3 in CG Gross Weight Zero Fuel Weight 2 120 369HE Moment at Gross Weight 240 865 101 3 ...

Page 213: ...ternal loadings are permissible if gross weight longitudinal and lateral center of gravity considerations permit For pilot and passenger lateral center of gravity see Figure 6 2 6 7 LATERAL LOADING OF CARGO To determine the gross weight and lateral center of gravity for a given flight are within limits proceed as follows Find weight of load Determine lateral location station of load center of grav...

Page 214: ...0 1 280 170 170 400 0 5 13 0 18 1 2 0 569 2 210 3 077 800 1 Zero Fuel Weight Add Fuel 1 878 400 0 58 0 1 098 0 2 020 400 0 54 0 1 098 0 2 Gross Weight 2 278 0 48 1 098 2 420 0 45 1 098 Calculation of Lateral CG CG Zero Fuel Weight 369HE Moment at Zero Fuel Weight 1 098 0 58 in Zero Fuel Weight 1 878 369HS Moment at Zero Fuel Weight 1 098 0 54 in CG Gross Weight Zero Fuel Weight 2 020 369HE Moment ...

Page 215: ...7 640 8 580 10 010 11 440 12 155 12 870 14 300 15 730 17 160 12 600 14 700 16 800 17 850 18 900 21 000 23 100 25 200 Baggage Weights and Longitudinal Moments Baggage Weight lb Moment in lb Utility Stowage Compartment Station 52 9 Under Seat and Center Station 110 Behind Seat Station 120 Fwd Bulkhead Station 87 10 20 30 40 50 60 70 80 90 100 529 1 058 1 587 2 116 2 645 1 100 2 200 3 300 4 400 5 500...

Page 216: ...ilot L H Station 13 0 Passenger R H Fwd Station 18 1 Passenger Center Fwd Station 2 6 Aft Passenger R H and L H Station 12 1 120 140 160 170 180 200 220 240 1 560 1 820 2 080 2 210 2 340 2 600 2 860 3 120 2 172 2 534 2 896 3 077 3 258 3 620 3 982 4 344 312 364 416 442 468 520 572 622 1 452 1 694 1 936 2 057 2 178 2 420 2 662 2 904 Baggage Weights and Lateral Moments Baggage Weight lb Station 12 8 ...

Page 217: ...hows typical tiedown for 500 pound cargo Restraint loops are to be secured as indicated and tied to the cargo to pre vent slippage of the loops Variations of the tiedown are allowable providing total restraint require ments are met Caution should be exercised to keep the cargo from bearing against the cen ter slanted portion of the aft bulkhead Table 6 4 Cargo Weight vs Loop Restraint Number of Re...

Page 218: ...ANUAL CSP HE HS 1 Weight and Balance Data Revision 6 6 21 6 22 blank VIEW I I I VIEW SHOWING LOCATION OF CARGO TlEDOWN POlNTS AND LOOPS MINIMUM LOOP STRENGTH 1800 LB VIEW II VIEW SHOWING 500 LB CARGO RESTRAINED F01 066 Figure 6 8 Cargo Restraint ...

Page 219: ......

Page 220: ...ure 7 2 Ground Handling Wheels 7 5 Moving and Towing Helicopter 7 3 7 4 7 6 Parking and Mooring 7 4 Figure 7 3 Parking and Mooring 7 6 7 7 Servicing General 7 7 Table 7 1 Servicing Materials Operating Supplies 7 7 Figure 7 4 Servicing Points 7 11 7 8 Fuel System Servicing 7 12 7 9 Engine Oil System Servicing 7 10 Main Rotor Transmission Servicing 7 11 Tail Rotor Transmission Servicing 7 13 7 13 7 ...

Page 221: ...FLIGHT MANUAL Revision 6 7 i 7 ii blank 7 16 Fluid Leak Analysis 7 15 7 17 Main Rotor Blade Leading Edge Abrasion Tape 7 16 7 18 Preservation and Storage 7 16 7 19 Flyable Storage No Time Limit 7 17 7 20 Engine Compressor Wash 7 18 ...

Page 222: ......

Page 223: ...28 volt direct current power with sufficient amperage rating may be used Before connecting external power be sure that helicopter main electrical power selector switch is OFF After power is connected to receptacle power switch must be set to EXT PWR position to connect external power to helicopter electrical system 7 3 HOISTING JACKING AND LIFTING Hoisting lifting and jacking of the helicopter sha...

Page 224: ...ROTOR HORIZONTAL STABILIZER UPPER VERTICAL STABILIZER LOWER VERTICAL STABILIZER TAIL BOOM TAIL ROTOR TRANSMISSION AFT SECTION FLIGHT CONTROLS TAIL ROTOR FORWARD SECTION MAIN TRANSMISSION POWER TRAIN ENGINE ENGINE ACCESS DOOR CARGO DOOR LOWER SECTION PILOT DOOR LANDING GEAR F01 015 Figure 7 1 Helicopter Major Components ...

Page 225: ... for moving the helicopter by hand and for towing The wheels are manually lowered with a detachable jack han dle and are held in the down position helicopter raised on wheels by a me chanical lock The wheels are equipped with tow bar attach fittings Attach ground handling wheels and hold tail up when lowering the wheels raising helicopter Figure 7 2 Ground Handling Wheels F01 046 ...

Page 226: ...t ends of skid tubes from dragging have an assistant balance helicopter at tailboom 7 6 PARKING AND MOORING Parking Ref Figure 7 3 To prevent rotor damage from blade flapping droop stop pounding CAUTION as a result of air turbulence from other aircraft landing taking off or taxiing or sudden wind gusts rotor blades should be secured whenever helicopter is parked Locate helicopter slightly more tha...

Page 227: ...uld be hangared or evacuated to safer area If these precautions are not possible moor helicopter as follows Park helicopter and remove main rotor blades and install air inlet fair ing and engine exhaust covers Install pitot tube cover Fill fuel tank if possible Apply friction to lock cyclic and collective sticks Secure helicopter to ground by attaching restraining lines cable or rope between jack ...

Page 228: ... TIEDOWN TETHER MOORING ANCHOR 4 PLACES CABLE OR MANILA ROPE PITOT TUBE COVER 369H4009 ENGINE EXHAUST OUTLET COVER 369H9804 AIR INLET FAIRING COVER 369H9803 EXTENSION SPRING ZIPPER ACCESS DOOR LATCH REF JACK FITTING LOCKPIN FUEL CELL ACCESS DOOR TYPICAL 2 PLACES LOCKPIN STOWAGE TIE CORD TO BLADE SOCK TO MOORING ANCHOR TO BLADE SOCK FUSELAGE STRUCTURE JACKING FITTING F01 048 Figure 7 3 Parking and ...

Page 229: ...ransmission Capacity 4 0 US Quarts 3 78 liters Use the materials listed under Item 3 or Mobil SHC 626 3 Engine Capacity 3 0 US Qt 2 84 liters Ambient Temperature Oil Type 0 C 32 F and above MIL PRF 23699C or subsequent preferred 0 C 32 F to 40 C 40 F MIL PRF 23699C or subsequent preferred or MIL PRF 7808G or subsequent 40 C 40 F and below MIL PRF 7808G or subsequent only Specification Material Man...

Page 230: ...t Hanover NJ 07936 Hatcol 3211 Hatco Corporation King George Post Road Fords New Jersey 08863 BP Turbo Oil 2380 EXXON Turbo Oil 2380 Air BP Castrol Aero Jet5 Castrol Industrial North Amer ica Specialty Products Division 5511 District Blvd Los Angeles CA 90040 MIL PRF 23699F Series Mobil Jet 254 and Mobil Jet 291 Aeroshell Royco Turbine Oil 560 Aeroshell Turbine Oil 560 BPTO 2197 Exxon ETO 2197 Hat...

Page 231: ...el No 1 conforming to ASTM D 1655 Jet A or Jet A 1 MIL DTL 83133 grade JP 8 CAUTION At 4 4 C 40 F and below fuel must contain anti icing additive that meets MIL I 27686 requirements For blending information and authorized fuels refer to the appropriate Rolls Royce Operation and Maintenance Manual 5 Overrunning Clutch Capacity 11 21 31 1 52 U S Oz 45cc 41 51 1 01 U S Oz 30cc Use the materials liste...

Page 232: ...Gear Value in excess of 2500 pounds per inch 2 Not a preferred lubricant for transmissions Use MIL PRF 7808 lubricating oil in transmission only when other oils are not available 3 For Model 250 Series engine oil change requirements and restrictions on mixing of oils refer to Rolls Royce Operation and Maintenance Manual DO NOT use Mobil SHC 626 oil in 250 Series engines WARNING Only discretionary ...

Page 233: ...T GAUGE OVERBOARD OIL DRAIN LINE ENGINE ACCESSORY GEARBOX DRAIN BREATHER FILLER BATTERY ONE WAY LOCK RESERVOIR FUEL SUPPLY LINE DRAIN VALVE TAIL ROTOR TRANSMISSION SIGHT GAUGE OIL SYSTEM DRAIN VALVE ENGINE OIL TANK FILLER EXTERNAL POWER RE CEPTACLE TAIL ROTOR TRANSMIS SION DRAIN GROUND RE CEPTACLE ENGINE WASH FITTING IF INSTALLED FUEL SYSTEM FILLER FUEL CELL S DRAIN VALVE F01 044 Figure 7 4 Servic...

Page 234: ...rade JP 5 and grade JP 8 MIL T 3133A or later type fuels contain anti ice additive which conforms to MIL 1 27686 or later These fuels do not require additional anti ice additive Cold weather fuel mixtures When operating at or below 4 C 40 F a mixture of AVGAS and jet fuels other than JP 4 or Jet B may be used in a ratio of one part by volume AVGAS to two parts by volume commercial jet fuel Refer t...

Page 235: ...ect oil until oil level is FULL on sight gauge CAUTION DO NOT use Mobil SHC 626 oil in the engine oil system NOTE To avoid possible foaming of oil and or engine oil pressure fluctuation shake oil can thoroughly to mix anti foam agent before filling engine oil system Make certain that oil tank filler cap is securely tightened immediately after servicing 7 10 MAIN ROTOR TRANSMISSION SERVICING Check ...

Page 236: ...eposits from the helicopter by using dry cleaning solvent standard commercial grade kerosene or a solution of deter gent soap and water Exceptions that must be observed are specified in the following cleaning para graphs 7 13 CLEANING FUSELAGE INTERIOR TRIM AND UPHOLSTERY Clean dirt or dust accumulations from floors and other metal surfaces with vacuum cleaner or small hand brush Sponge soiled uph...

Page 237: ...insing with clean water Use mild soap and water solution or aircraft type plastic cleaner to remove oil spots and similar residue Never attempt to dry plastic panels with cloth To do so causes CAUTION any abrasive particles lying on plastic to scratch or dull surface Wiping with dry cloth also builds up an electrostatic charge that attracts dust particles from air After dirt is removed from surfac...

Page 238: ...in service can cause inter nal damage that might not otherwise occur NOTE It is normal for a thin hydraulic oil film to remain on damper piston as a result of wiping contact with piston seal Newly installed dampers may also have slight oil seepage from oil trapped in end cap threads during damper assembly Neither of these should be considered damper leakage or cause from damper replacement 7 17 MA...

Page 239: ...rm daily inspection ground ru nup must be performed at least once every 5 days Perform daily pre flight check Start engine Section IV After idle stabilizes accelerate engine to flight idle Operate until oil temperature shows an increase and ammeter reads zero Replenish fuel as necessary Open movable air vents in each cargo door positioning air vent openings downward Install covers and equipment us...

Page 240: ...er generator can be used to motor the Allison 250 Series engine for compressor cleaning cycle Input voltage should be 24 vdc but it is permissible to use 12 vdc To prevent starter generator damage duty cycle cranking time limits that must not be exceeded are 24 vdc External Auxiliary Power 24 vdc Helicopter Battery Power 25 Seconds ON 30 Seconds ON 30 Seconds OFF 2 Minutes OFF 25 Seconds ON 30 Sec...

Page 241: ...seconds prior to starter engagement e Motor the engine with the twistgrip in CUTOFF e Release starter switch as necessary to maintain between 5 and 10 N1 speed during the wash rinse e Water injection will continue during coast down until N1 stops e Allow engine to drain e Within 15 minutes of the water rinse operate the engine at idle for five minutes and actuate anti ice cabin heat and scav air i...

Page 242: ......

Page 243: ...on Strips Installed Takeoff Power Allison 250 C20 Figure 8 2 Hover Ceiling Vs Temperature OGE Utility Floats Tail Rotor Abrasion Strips Installed Takeoff Power Allison 250 C20 Figure 8 3 Hover Ceiling Vs Temperature OGE Utility Floats 8 1 8 3 8 4 Takeoff Power Allison 250 C20 Hover Ceiling Vs Temperature OGE Takeoff Power 8 4 Allison 250 C18 Figure 8 4 Hover Ceiling Vs Temperature OGE Utility Floa...

Page 244: ......

Page 245: ...s described in Section V OGE hover performance table An OGE hover perfromance table is provided for 369HE HS helicopters equipped with Allison 250 C20 engines Ref Table 9 1 This table may be used for planning flights with external loads When using this table for OGE hover data with internal loads the maximum certified gross weight is limited to 2550 LBS Weights above 2550 LBS must be external and ...

Page 246: ... TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER ALT FT SEA LEVEL TO HEAT ICE AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER 12 000 112 120 236 INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 97 106 83 89 206 175 20 000 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL...

Page 247: ...AFT FLIGHT MANUAL CSP HE HS 1 Additional Operations and Performance Data Revision 6 8 3 MBIENT TEMPERATURE DEGREES C Figure 8 1 Hover Ceiling Vs Temperature OGE Tail Rotor Abrasion Strips Installed Takeoff Power Allison 250 C20 F01 076 ...

Page 248: ... MAIN ROTOR ABRASION TAPE INSTALLED 3 REDUCE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD 6 000 18 000 OAT C 5 15 35 WT LBS 2 5 7 16 000 GROSS WEIGHTS ABO...

Page 249: ...Revision 6 8 5 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Additional Operations and Performance Data Allison 250 C20 F01 077 ...

Page 250: ...CE HOVER CEILING 400 FT ABOVE CRITICAL ALTITUDE OVER AND ALT FT SEA LEVEL TO HEAT ICE ABOVE ANY OTHER HOVER REDUCTION FOR ANY OTHER INSTALLED KIT 12 000 132 144 288 20 000 OR BASIC AIRCRAFT WHEN THE PARTICLE SEPARATOR IS INSTALLED 16 000 20 000 116 98 123 108 250 217 6 000 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD O...

Page 251: ...sion 6 8 7 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Additional Operations and Performance Data Figure 8 3 Hover Ceiling Vs Temperature OGE Utility Floats Takeoff Power Allison 250 C20 ...

Page 252: ...GE AIR ON 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED SEA LEVEL TO 10 000 15 000 20 000 125 105 85 155 130 105 290 240 195 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR D 6 000 IN 16 000 5 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 4 000 3 000 2 000 1 000 GROSS WEIGHTS ABOVE 2550 LB MUST ...

Page 253: ...Revision 6 8 9 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Additional Operations and Performance Data igure 8 4 Hover Ceiling Vs Temperature OGE Takeoff Power Allison 250 C18 F01 067 ...

Page 254: ... 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED SEA LEVEL TO 10 000 15 000 20 000 125 105 85 155 130 105 290 240 195 18 000 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR ELECTRICAL LOAD 6 000 INCR O EA A TS E C IN WT 5 15 35 2 5 7 16 000 5 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 4 000 3 000 2 000 1 000 GROSS WEIGHTS ABOVE 2550 LB MUST BE EX...

Page 255: ...ion 6 8 1 1 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Additional Operations and Performance Data Figure 8 5 Hover Ceiling Vs Temperature OGE Utility Floats Takeoff Power Allison 250 C18 ...

Page 256: ...2485 2450 2320 2160 1940 10000 3048 2580 2550 2515 2470 2460 2365 2220 2065 1850 11000 3353 2550 2520 2480 2435 2380 2265 2130 1980 1770 12000 3658 2520 2490 2450 2395 2285 2165 2035 1890 1680 13000 3962 2475 2450 2385 2290 2190 2080 1950 1805 1600 14000 4267 2450 2370 2285 2200 2110 1990 1870 1725 15000 4572 2355 2275 2195 2110 2020 1910 1790 1645 16000 4877 2250 2175 2100 2025 1935 1830 1710 157...

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Page 258: ...t 9 5 Figure 9 1 Cargo Hook Release Electrical and Mechanical 9 7 Figure 9 2 Cargo Hook 9 9 Table 9 3 Cargo Hook Loading Data 9 10 9 6 Operating Instructions Anti Ice Fuel Filter 9 11 Figure 9 3 Anti Ice Airframe Fuel Filter 9 13 Figure 9 4 Anti Ice Fuel Filter Switch and Indicator Panel 9 14 9 7 Operating Instructions Cargo Swing 9 17 Table 9 4 Cargo Hook Loading Data 9 20 9 8 Operating Instructi...

Page 259: ... Instructions Rotorcraft Litter 9 35 Figure 9 6 Variation of VNE With Altitude 9 37 Figure 9 7 VNE Placard 9 37 Figure 9 8 Best Rate of Climb Speed Figure 9 9 Indicated Airspeed Vs Calibrated Airspeed 9 12 Operating Instructions Luggage Pod 9 13 Operating Instructions Search Light 9 39 9 40 9 43 9 45 FAA Approved Revision 6 9 i ...

Page 260: ...ng Limitations 250 C18 Engine 9 48 9 15 Operating Instructions Automatic Reignition 9 51 Figure 9 11 Auto Reignition Switch Panel Locations 9 53 9 16 369HM Configuration 9 59 Figure 9 12 Warning and Caution Indicators Typical 9 60 Figure 9 13 Type T Instrument Panel Layout Typical Figure 9 14 Electrical Controls Console Layout Typical 9 61 9 62 Figure 9 15 Cyclic Grip 9 62 ...

Page 261: ...MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment 9 ii FAA Approved Revision 6 ...

Page 262: ...ion Procedures Section III Normal Pro cedures Section IV and Performance Data Section V The Flight Manual Supplemental Data is to be used in conjunction with the basic Flight Manual data and takes precedence over that data when the equip ment is installed Be sure to include a review of the appropriate flight manual CAUTION supplemental data for type of optional equipment installed including STC it...

Page 263: ... Hook Hoist Utility Floats Emergency Floats Searchlight Anti Ice Fuel Filter Engine Air Deflector 369H90006 369H90123 369A9005 369H90148 369H90034 369H90115 369H90118 369H90002 369H90011 369H90017 369H90065 369H90072 369H90070 369H90086 369H90121 369H90142 369A90022 M30287 CSP HE HS 1 CSP HE HS 1 CSP HE HS 1 CSP HE HS 1 CSP HE HS 1 Section IX Section IX Section IX Section IX Section IX Section IX ...

Page 264: ...on extended landing gear 6 Not compatible if installed on standard landing gear The Anti Ice Fuel filter is approved for use on 369HE HS helicopters equipped with the 250 C20 engines only and may be used in combination with all other approved optional equipment Emergency floats on standard landing gear may not be installed with 369H90062 5 and 6 step assemblies components of the night flying kit T...

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Page 266: ...p to 1800 pounds When the kit is installed an owner or operator holding a valid Rotorcraft Ex ternal Load Operator Certificate may utilize the helicopter for transportation of external cargo when operated by a qualified pilot OPERATIONS WITH CAR GO ON THE HOOK SHALL BE CONDUCTED IN ACCORDANCE WITH APPLICABLE PORTIONS OF FEDERAL AVIATION REGULATIONS PART 133 Information provided in these operating ...

Page 267: ...ctural load limit is 1800 pounds Airspeed Limitations With no load on hook airspeed limits are unchanged With load on hook airspeed limits are presented on the external load VNE placards NOTE Use caution as size and shape of load and load attaching cable size and length may affect flight characteristics Satisfactory flight characteristics have been demonstrated with a compact load For operations a...

Page 268: ...ate mechanical release handle to release cargo in the event of an elec trical failure Operate handle quickly and deliberately NOTE Ground support personnel should manually assure positive reset of the cargo hook after use of mechanical release prior to further cargo pickups Static Electricity Discharge Instruct ground crew to insure that the helicopter has been electrically grounded prior to attac...

Page 269: ...ks Check electrical and emergency operation of cargo release Check operation of external release knob located on left side of cargo hook body Hook should return to the closed position after above checks Move pilot s cyclic to all extreme positions Cargo hook must remain locked and external release knob must not rotate With load ring in cargo hook swing hook to the limits of trav el in all directio...

Page 270: ...Kit FAA Approved Revision 6 9 9 EXTERNAL RELEASE TURN CLOCKWISE ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK LOAD BEAM F01 071 Figure 9 2 Cargo Hook PART V PERFORMANCE DATA Refer to Section V for IGE Hover Ceiling vs Temperature and Section VIII for OGE Hover Ceiling vs Temperature ...

Page 271: ...ata should be used by the opera tor to assist in evaluating the helicopter center of gravity for various hook load weights Cargo Hook Loading Data Table 9 3 Cargo Hook Loading Data Cargo Longitudinal CG 99 3 In Cargo Weight lb Moment 100 in lb 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 1800 99 199 298 397 497 596 695 794 894 993 1092 1191 1291 1390 1490 1589 1688 1...

Page 272: ...articles and other solid contaminants from the fuel prior to entering the engine fuel system Installation of the filter will delete the requirement for use of fuel containing anti ice additives The filter unit is mounted on the aft face of the firewall ahead of the engine fuel pump inlet and contains a 10 micron 500 square inch disposable filter ele ment A pressure sensing switch in the filter bod...

Page 273: ...e maximum but not to exceed limitations of Basic RFM Section II Anti Ice fuel Additives Installation of the Anti Ice Airframe Fuel Filter eliminates the need for anti ice fuel additives in the fuel i e Prist Placards ANTI ICE FUEL FILTER INSTALLED For ground temperature of 5 C or less max ALT 12 000 ft For ground temperature greater than 5 C max ALT 14 000 ft PART III EMERGENCY AND MALFUNCTION PRO...

Page 274: ... is ON An unexpected flameout or power loss may occur if air is allowed to enter the fuel system NOTE If aircraft has been exposed to freezing temperatures failure to drain may be due to ice in filter element e Drain filter from valve on bottom of filter unit NOTE The following checks should be performed as part of the engine compartment checks listed in the basic preflight checklist in Section IV...

Page 275: ...UEL FILTER light is illuminated depress to ensure that system is re set Depress red press to test button located on the top of the fuel filter hous ing hold for 5 seconds FUEL FILTER and start pump lights should illumi nate Release the press to test button FUEL FILTER and start pump lights should remain on Depress FUEL FILTER caution light on panel FUEL FILTER and start pump light should go out Ca...

Page 276: ...ght NOTE Once system is activated it will remain on until manually reset by pressing FUEL FILTER caution light Icing may be verified by momentary depressing the FUEL FILTER caution light If the caution light does not re illuminate in approximately 3 seconds pull and reset the FUEL ANTI ICE circuit breaker to verify that icing conditions do not exist Post Flight Filter Cleaning When ambient tempera...

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Page 278: ...to pro vide the pilot with cargo release or jettison capability using a switch on the cy clic stick and manual backup release mechanism The cargo hook is automati cally stowed when not in use The cargo swing kit is designed to carry hook loads up to 1400 pounds When the kit is installed an owner or operator holding a valid Rotorcraft Ex ternal Load Operator Certificate may utilize the helicopter f...

Page 279: ...ions are unchanged With no load on hook and hook not stowed 80 knots or basic helicopter VNE whichever is less With load on hook use caution since size and shape of load may effect con trollability Operator must establish airspeed limits in accordance with FAR part 133 Placards Make placards stating approved load class es and occupancy limitations display placards in a conspicuous location in cabi...

Page 280: ...licopter has been electrically grounded prior to attaching cargo to drain charges of static electricity that may build up in flight PART IV NORMAL PROCEDURES Normal Operations Check cargo release circuit breaker IN Activate cargo release arming switch Use care to avoid passing load attaching cables over landing gear CAUTION skid tube when attaching load to hook with helicopter on ground Apply coll...

Page 281: ...on V for IGE Hover Ceiling vs Temperature and Section VIII for OGE Hover Ceiling vs Temperature PART VI WEIGHT AND BALANCE DATA Weight and Loading The following table of Cargo Swing Loading Data should be used by the op erator to assist in evaluating the helicopter center of gravity for various hook load weights Table 9 4 Cargo Hook Loading Data Cargo Longitudinal CG 96 9 Cargo Weight lb Moment in...

Page 282: ...nto the engine air inlet of foreign objects which are of sufficient mass to puncture the inlet screen particle separator and damage the engine The kit includes a hub and engine air inlet cover to inhibit the entrance of snow and water while the helicopter is parked PART III EMERGENCY AND MALFUNCTION PROCEDURES Air Restart Engine Follow the emergency air restart procedure as described in Section II...

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Page 284: ...n required The switch actuates valves allowing air stored in cylinders within the float package to inflate the An optional Night Landing Lighting Kit is available as an aid to landing on water at night It consists of dual belly mounted sealed beam lights a circuit breaker and a three position switch installed on the collective control Switch forward position activates the standard nose mounted lan...

Page 285: ...mbination Limitations Emergency floats on standard landing gear may not be installed with 369H90062 5 and 6 step assemblies which are components of the night lighting kit When the 369H90060 passenger step kit is installed in combination with the emergency floats the steps must be removed prior to over water flight Type of Operation Night flight over water beyond autorotation capability to ground i...

Page 286: ...9 5 Operational Temperature Float Inflation Time Altitude Required For Deployment Up to 70 F 21 C Above 70 F 9 0 sec 6 3 sec 330 feet 250 feet 50 EXAMPLE IF IN A 55 ENVIRONMENT THE GAUGE PRESSURE IS READ AT 3100 40 PSIG THE MINIMUM FLOAT OPERATIONAL TEMPERATURE IS 5 F 30 20 PRESSURE PSIG 3000 10 0 10 20 3100 3200 3300 3400 25 30 0 10 20 30 40 50 60 70 80 90 TEMPERATURE AT TIME OF READING PRESSURE ...

Page 287: ...or over water operation in the crossed hatch area of the Height Veloc ity Diagram immediate pilot reaction will be required to ensure float inflation prior to water contact Make a normal landing approach Minimize forward speed prior to water contact Recommended water contact speed 10 knots or less Do not low er collective until forward speed is 5 knots or less Landings have been demonstrated at gr...

Page 288: ...roximately as tabulated below per 1 F 1 C increase decrease in temperature of the pressure ves sel See Figure 1 to verify that pressure is adequate for the anticipated mini mum operating temperature Charge Pressure Psig F Psig C 3000 3100 3500 5 7 5 9 6 6 10 2 10 5 11 9 Set BATTERY EXT switch in proper position BATTERY when using ro torcraft battery EXT when using an external power source Close em...

Page 289: ... 104 0 3 0 3 0 3 0 Emergency Floats 369H90121 511 on standard landing gear as follows Gross Weight lb Longitudinal C G Limit Sta in Lateral C G Limit Sta in Forward Aft Right Left 2001 to 2250 2000 and below 99 0 97 0 104 0 104 0 3 0 3 0 Emergency floats 369H90121 505 on extended landing gear Longitudinal limits Station 99 to 103 Lateral limits 3 inches Weight and station data for the float kit af...

Page 290: ...ed with a recessed cable cutter button on the cyclic stick The hoist oper ator is provided with a safety harness a three position switch to raise or lower the cable and a guarded cable cutter button The cable cutter is a redundant circuit electrically initiated pyrotechnic device A door hold open is provided for use during hoisting operation When the kit is installed an owner or operator holding a...

Page 291: ...5 0 5 5 5 0 is right of centerline is left of centerline when looking forward For all other operations with hoist cable stowed same as those for the basic helicopter Fuel system limitations When using the center of gravity limits specified for hoisting operations us able fuel is reduced to 63 US gallons 239 liters for non self sealing fuel tanks and to 61 US gallons 230 liters for self sealing fue...

Page 292: ...e hoist must be removed prior to hoisting operations Operations combining cargo hook cargo swing loads with the hoist is not permitted Placards Make placards stating approved load class es and occupancy limitations display placards in conspicuous location in cabin NOTE 300 pounds is the allowable loading limit on the hoist hook Placard stating External Load Limit 300 Pounds installed on the hook P...

Page 293: ...st operations site bring the hook over the door as the door is opened slide the bar latch into door slot to lock door in open posi tion attach electrical connector to hoist Operator may move cable up or down by means of the three position switch provided in the cargo compartment NOTE Any time that the cable is extended limit speed to 20 mph or less Prior to moving away from hoist operation site th...

Page 294: ... Pounds Forward Passenger Weight Pounds Attendant Weight Pounds 150 175 200 225 Permissible Hoist Loads Pounds A 150 0 150 175 200 225 300 295 280 265 245 300 285 270 250 235 300 275 255 240 225 300 260 245 230 215 B 175 0 150 175 200 225 300 300 300 285 270 300 300 290 275 260 300 295 280 265 250 300 285 270 255 240 C 200 0 150 175 200 225 300 300 300 300 295 300 300 300 300 280 300 300 300 290 2...

Page 295: ...t Weight 175 Pounds Forward Passenger Weight 0 Pounds Find Permissible Hoist Load Consult Table I Part B for the given weights The maximum allowable hoist load is 300 pounds NUMBER 2 Pilot Weight 225 Pounds Attendant Weight 150 Pounds Forward Passenger Weight 150 Pounds Find Permissible Hoist Load Consult Table I Part D for the given weights The maximum allowable hoist load is 300 pounds ...

Page 296: ... porting one or two litter patients as well as one or two attendants in the cargo compartment of the helicopter The kit consists of two litters folding litter sup port structure attaching hardware and two special doors The special doors incorporate provisions for quick installation of bubble windows which permit high speed and or long distance transportation of patients and attendants in comfort A...

Page 297: ...talled the basic flight manual limitations apply If the litters are removed and the bubble glass door panels remain limita tions stated in these operating instructions apply Gross Weight Limitations Maximum gross weight with the litter kit installed is 2539 pounds for heli copters with the the 250 C18 engine installed with the 250 C20 engine no change Center of Gravity Limitations Center of gravit...

Page 298: ...12 000 10 000 8 000 6 000 4 000 2 000 0 60 80 100 INDICATED AIRSPEED KNOTS F01 052 Figure 9 6 Variation of VNE With Altitude VNE WITH BUBBLE DOORS 369H90085 PRESS ALT VNE KNOTS IAS X 1000 C OAT 30 15 0 15 30 45 G W UP TO 2536 LBS 0 1 4 7 10 13 113 104 95 85 77 68 61 86 76 67 59 50 167 58 49 104 95 87 79 111 103 105 97 369H6528 511 Figure 9 7 VNE Placard ...

Page 299: ...e litters are installed operations must be conducted with the bubble glass window panels installed and performance will be as noted in the following paragraphs Hover Performance Reduce hover performance by 14 pounds with litter kit installed in basic he licopter or in combination with other optional equipment items ie Utility Float Kit Speed for Best Rate of Climb The variation of speed for best r...

Page 300: ...TORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Rotorcraft Litter DENSITY ALTITUDE FEET18000 16000 2000 LB OR LESS 14000 12000 10000 MORE THAN 2000 LB 8000 6000 4000 2000 0 0 10 20 30 40 50 60 70 INDICATED AIRSPEED CORRECTED FOR INSTRUMENT ERROR F01 051 ...

Page 301: ...FAA Approved Revision 6 9 40 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Rotorcraft Litter Figure 9 8 Best Rate of Climb Speed ...

Page 302: ...CRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Rotorcraft Litter CALIBRATED AIRSPEED KNOTS 120 110 100 90 80 70 60 50 40 30 20 10 0 0 10 20 30 40 50 60 70 80 90 100 110 120 INDICATED AIRSPEED KNOTS F01 050 Figure 9 9 Indicated Airspeed Vs Calibrated Airspeed ...

Page 303: ...positioned indiscriminately for any combination under seven provided the gross weight of 2536 pounds with 250 C18 engine or 2550 pounds with 250 C20 engine is not exceed ed Some loading conditions may result in a limitation to the fuel supply Substantial differences in the weight of the passengers will necessitate a weight and balance analysis to assure center of gravity limits are main tained The...

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Page 305: ... the pods to facilitate entry to the passenger compartment PART II LIMITATIONS Weight Limitations Maximum allowable weight in each pod is 250 pounds Do not exceed 60 pounds per square foot load density in pods Helicopter center of gravity including effect of pod and load in pod must not exceed the helicopter center of gravity Section VI Kit Combinations Limitations The 369H90070 Rotorcraft Hoist K...

Page 306: ...Litter kit re duce hover performance capability by 25 pounds With the Luggage Pod Kit installed in combination with any other kit that reduces hover performance capability the sum of the reduced weight capa bilities for each kit shall be applied to determine hover capability PART VI WEIGHT AND BALANCE DATA Weight and Loading ITEM WEIGHT Lbs STATION In Luggage Pod ea 30 7 99 1 A weight and balance ...

Page 307: ...light assemblies mounted below the cockpit a handle which protrudes through the cockpit floor and provides for operation of the searchlight in flight a warning light which indicates when the lights are extended and the necessary structural support and electrical system PART II LIMITATIONS Kit Combination Limitations The search light control handle must be in the stowed handle forward position when...

Page 308: ... locked position Prior to landing assure that the searchlight is in the stowed position warning light out During inflight searchlight operations the operator should use care to avoid glare and reflections on the canopy that may distract the pilot When the searchlight kit is installed with utility floats the lights should not be turned on until fully extended and care should be exercised to avoid p...

Page 309: ...nter position is off and aft position illuminates the the belly lights Night flight over water is permitted with the night landing light kit installed PART II LIMITATIONS Weight Limitations NOTE Figure 9 10 does not apply to helicopters equipped with the optional aluminum tail rotor kit or with the 250 C20 engine installed Maximum gross weight is 2515 pounds with 250 C18 engine installed See Figur...

Page 310: ...ORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Utiltiy Floats PRESSURE ALTITUDE FEET 22 000 20 000 18 000 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 0 50 40 30 20 10 0 10 20 30 TEMPERATURE DEGREES C 40 20 0 20 40 60 TEMPERATURE DEGREES F F01 054 ...

Page 311: ...FAA Approved Revision 6 9 49 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Utiltiy Floats Figure 9 10 Takeoff and Landing Limitations 250 C18 Engine ...

Page 312: ...iations in ambient temperature or water temperature at a given base of operations the following criteria should be used to maintain the minimum 1 5 psig inflation pressure When an ambient air temperature or water temperature colder than the tem perature at initial inflation is anticipated float inflation pressure should be in creased 0 5 psig above minimum 1 5 psig for each 15 degrees decrease in ...

Page 313: ...stacle during these operations Tail swing before directional control is ob tained during engagement will be approximately 200 degrees nose right and 200 degrees nose left during rotor brake application Landing Water landing speed should be 20 knots or less Touchdown with a slightly tail low attitude Water taxi speed should be less than 10 mph It will be necessary to in crease collective pitch to t...

Page 314: ...nating the RE IGN indicator light in the cockpit and energizing the engine ignition exciter to reignite the engine Later unmodified System 250 C18 or C20 The system consists of a modification to the Engine Failure Low Rotor Speed Warning sensing unit a guarded arming switch and two indicator lights on the instrument panel in the cockpit plus the necessary electrical components and wiring to connec...

Page 315: ...wing snow is only permitted with the center front seat occupied following completion of HN 160 Placards The following placard is to be located in view of the pilot and in close prox imity to the automatic reignition arming switch if HN 160 has not been completed MIDDLE FRONT SEAT IS NOT TO BE OCCUPIED DURING FLIGHT INTO FALLING OR BLOWING SNOW NOTE The above placard is not required if the helicopt...

Page 316: ...SHOWN WITH SWITCH GUARD REMOVED OFF EARLY INSTRUMENT PANEL WITH LATER MODIFIED AUTO REIGNITION SYSTEM SWITCH AND INDICATOR PNEL PRESS TO RESET RE IGN ARMED AUTO REIGN TEST OFF EARLY INSTRUMENT PANEL PRESS TO RESET RE IGN ARMED LATER MODIFIED AUTO REIGNITION SWITCH AND INDICATOR PANEL AUTO REIGN TEST OFF AUTO REIGN ARM OFF RE IGN ARMED PRESS TO RESET EARLY UNMODIFIED AUTO REIGNITION SWITCH AND INDI...

Page 317: ...FAA Approved Revision 6 9 55 MD 500 Models 369HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment Automatic Engine Reignition Figure 9 11 Auto Reignition Switch Panel Locations ...

Page 318: ...uld illuminate indicating operation of the ignition igniter e If it is desired to extinguish the RE IGN light increase engine torque pressure to approximately 40 psi Press and release RE IGN light Light should go out e Arm the system any time falling or blowing snow is encountered NOTE Each time the engine torque pressure falls below 25 psi with the system ARMED the amber RE IGN indicator will ill...

Page 319: ...educe RPM to below 98 percent The RE IGN light should illuminate indicating that the ignition igniter has been energized e If it is desired to extinguish the RE IGN light press and release RE IGN light Light should go out e If continued operation of the system is not desired disarm the system Arm the system any time falling or blowing snow is encountered Each time that the engine failure low rotor...

Page 320: ...D and RE IGN indicators illuminate and the sound of the igniter firing is heard e Release test switch Only the RE IGN light should remain illuminated after the test switch is released e Press RE IGN light to reset the light Engine Run up NOTE The RE IGN light may illuminate when the XMSN OIL PRESS light goes out After flight rpm is established press the RE IGN light to reset extinguish the light W...

Page 321: ...rdance with the appropriate Alli son 250 Series Operation and Maintenance Manual System Checks following completion of TB369H 004 NOTE The principle change to the system removes the manual reset requirement of the automatic reignition indicator light to automatic reset once the event that caused the reignition condition is not present Before engine start e Verify ARMED and RE IGN lights come on wh...

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Page 323: ...he same as the basic 369HE HS ex cept for dual flight controls right hand command self sealing fuel cells mesh seats for pilot co pilot and two canvas or nylon mesh passenger seats in the cargo compartment Additionally the helicopter may be equipped with the standard instrument panel Ref Section IV or a T instrument panel Ref Figure 9 13 PART II LIMITATIONS Flight restrictions The minimum flight c...

Page 324: ...d indicator light Warning and Caution annunciation The MASTER CAUTION light switch flashes at the same time any other warning or caution light is activated by a fault signal e g engine chips Pressing the MASTER CAUTION light switch resets turns off the flashing light Malfunction procedures Refer to Section III 1 2 3 4 5 6 7 8 9 10 11 12 13 14 1 DC GENERATOR GENERATOR OUT 2 ENGINE CHIPS 3 TRANSMISS...

Page 325: ...69HE HS HM ROTORCRAFT FLIGHT MANUAL CSP HE HS 1 Optional Equipment 369HM Configuration FAA Approved Revision 6 9 61 PART IV NORMAL PROCEDURES 0 o JO a 1 0 0 F01 078 Figure 9 13 Type T Instrument Panel Layout Typical ...

Page 326: ...ion FAA Approved Revision 6 9 61 CIRCUIT BREAKER PANEL PILOT S COLLECTIVE ASH TRAY AND LIGHTER SWITCH CONTROL PANEL LIGHTS CONTROL PANEL F01 079 Figure 9 14 Electrical Controls Console Layout Typical DWN L CARGO HOOK CYCLIC TRIM R RELEASE UP HOIST GUILLOTINE FLOATS INFLATION Figure 9 15 Cyclic Grip ...

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Summary of Contents for MILVIZ MD530F

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