MD Helicopters 369HE Flight Manual Download | Manualshive

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Optional Equipment

369HM Configuration

ROTORCRAFT FLIGHT MANUAL

MD 500

(Models 369HE/HS/HM

)

CSP-HE/HS-1

Revision 6

9-60

FAA Approved

PART III

EMERGENCY AND MALFUNCTION PROCEDURES

Warning and Caution indicators:

The caution and warning indicators consisting of thirteen indicator lights
and a PRESS−TO−TEST switch. The PRESS−TO−TEST non−lighted switch
is electrically connected to the caution and warning indicators for testing
indicator lights.

NOTE

:

The warning/caution indicators are not indicated by a yellow or red 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.

F01-080

1

2

3

4

5

6

7

8

9

10

11

12

13

14

1. DC GENERATOR (GENERATOR OUT)

2. ENGINE CHIPS

3. TRANSMISSION CHIPS

4. TAIL ROTOR TRANSMISSION CHIPS

5. FUEL LOW

6. FUEL FILTER

7.

*

START PUMP ON

8. BATTERY 140F

9. BATTERY 160F

10. TRANSMISSION OIL TEMPERATURE

11. ENGINE OUT

12. TRANSMISSION OIL PRESSURE

13. MASTER CAUTION

14. PRESS TO TEST

*INDICATES THAT START PUMP IS ON".

Figure 9-12. Warning and Caution Indicators - Typical

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Summary of Contents for 369HE

Page 1: ...Pages in the manual to ensure all prior revisions are inserted REMOVE PAGES INSERT PAGES FRONT MATTER F i F ii F i F ii F ix thru F xviii F ix thru F xviii SECTION I All pages New Revision 6 Pages SECTION II 2 11 thru 2 14 2 11 thru 2 14 SECTION III All Pages New Revision 6 Pages 4 5 4 6 SECTION IV 4 5 4 6 4 15 4 16 4 15 4 16 SECTION VI All pages New Revision 6 Pages SECTION VII All pages New Revi...

Page 2: ......

Page 3: ...FLIGHT MANUAL THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL CONSISTS OF THE FOLLOWING SECTIONS SECTION II LIMITATIONS SECTION III EMERGENCY PROCEDURES SECTION IV NORMAL PROCEDURES SECTION V PERFORMANCE DATA SECTION IX OPTIONAL EQUIPMENT The helicopter must be operated in compliance with the operating limitations as set forth in Section II of this manual and any additional limitations from Section IX a...

Page 4: ...9 369HE Configuration B 10 April 1972 Original Issue 369HM Configuration A 4 May 1970 369HM Configuration B 10 April 1972 Original 13 July 1998 Revision 1 12 November 1998 Revision 2 25 February 2000 Revision 3 22 May 2000 Revision 4 10 October 2000 Revision 5 22 March 2001 Revision 6 4 October 2006 Approved By______________________________ Manager Flight Test Branch ANM 160L Federal Aviation Admi...

Page 5: ...instrument cluster Paragraph 2 11 Updated fuel specification designations and added alternate fuels Section III Removed company logo from all pages Paragraph 3 9 Added malfunctions procedures for low engine oil pressure and loss of torque indication Section IV Paragraph 4 1 Added check for torque stripe paint across tail rotor retainer nut tang washer and fork assembly Paragraph 4 3 Corrected star...

Page 6: ...F iv Revision 5 F v Revision 5 F vi Revision 5 F vii F viii blank Revision 5 F ix Revision 6 F x Revision 6 F xi Revision 6 F xii Revision 6 F xiii Revision 6 F xiv Revision 5 F xv Revision 6 F xvi Revision 6 F xvii Revision 6 F xviii Revision 6 I 1 i 1 ii blank Revision 6 1 1 Revision 6 1 2 Revision 6 1 3 Revision 6 1 4 Revision 6 1 5 Revision 6 1 6 Revision 6 1 7 Revision 6 1 8 Revision 6 1 9 Re...

Page 7: ...sion 6 1 16 Revision 6 1 17 Revision 6 1 18 Revision 6 1 19 Revision 6 1 20 Revision 6 II 2 i 2 ii blank Revision 5 2 1 Revision 5 2 2 Revision 5 2 3 Revision 5 2 4 Revision 5 2 5 Revision 5 2 6 Revision 5 2 7 Revision 5 2 8 Revision 5 2 9 Revision 5 2 10 Revision 5 2 1 1 Revision 6 2 12 Revision 5 2 13 C Revision 5 2 14 C Revision 6 2 15 C Revision 5 2 16 Revision 5 2 17 Revision 5 2 18 Revision ...

Page 8: ...nal 3 3 Revision 6 3 4 Revision 6 3 5 Revision 6 3 6 Revision 6 3 7 Revision 6 3 8 Revision 6 3 9 Revision 6 3 10 Revision 6 3 1 1 Revision 6 3 12 Revision 6 3 13 Revision 6 3 14 Revision 6 3 15 Revision 6 3 16 Revision 6 3 17 Revision 6 3 18 Revision 6 3 19 Revision 6 3 20 Revision 6 3 21 Revision 6 3 22 Revision 6 3 23 Revision 6 3 24 Revision 6 3 25 Revision 6 3 26 Revision 6 3 27 Revision 6 3 ...

Page 9: ...n 5 4 2 Revision 5 4 3 Revision 5 4 4 Revision 5 4 5 Revision 5 4 6 Revision 6 4 7 Revision 5 4 8 Revision 5 4 9 Revision 5 4 10 Revision 5 4 1 1 Revision 5 4 12 Revision 5 4 13 Revision 5 4 14 Revision 5 4 15 Revision 6 4 16 Revision 6 4 17 Revision 5 4 18 Revision 5 4 19 Revision 5 4 20 Revision 5 4 21 Revision 5 4 22 Revision 5 4 23 Revision 5 4 24 Revision 5 4 25 Revision 5 4 26 Revision 5 4 2...

Page 10: ...n 5 5 4 Revision 5 5 5 Revision 5 5 6 Revision 5 5 7 Revision 5 5 8 Revision 5 5 9 Revision 5 5 10 Revision 5 5 1 1 Revision 5 5 12 Revision 5 5 13 Revision 5 5 14 Revision 5 5 15 Revision 5 5 16 Revision 5 5 17 Revision 5 5 18 Revision 5 5 19 Revision 5 5 20 Revision 5 5 21 Revision 5 5 22 Revision 5 5 23 Revision 5 5 24 Revision 5 5 25 Revision 5 5 26 Revision 5 5 27 Revision 5 5 28 Revision 5 5...

Page 11: ...6 6 1 Revision 6 6 2 Revision 6 6 3 Revision 6 6 4 Revision 6 6 5 Revision 6 6 6 Revision 6 6 7 Revision 6 6 8 Revision 6 6 9 Revision 6 6 10 Revision 6 6 1 1 Revision 6 6 12 Revision 6 6 13 Revision 6 6 14 Revision 6 6 15 Revision 6 6 16 Revision 6 6 17 Revision 6 6 18 Revision 6 6 19 Revision 6 6 20 Revision 6 6 21 6 22 blank Revision 6 VII 7 i 7 ii blank Revision 6 7 1 Revision 6 7 2 Revision 6...

Page 12: ... 1 1 Revision 6 7 12 Revision 6 7 13 Revision 6 7 14 Revision 6 7 15 Revision 6 7 16 Revision 6 7 17 Revision 6 7 18 Revision 6 7 19 7 20 blank Revision 6 VIII 8 i 8 ii blank Revision 6 8 1 Revision 6 8 2 Revision 6 8 3 Revision 6 8 4 Revision 6 8 5 Revision 6 8 6 Revision 6 8 7 8 8 blank Revision 6 IX 9 i Revision 6 9 ii Revision 6 9 1 Revision 6 9 2 Revision 6 9 3 Revision 6 9 4 9 5 blank Revisi...

Page 13: ...nk Revision 6 9 17 Revision 6 9 18 Revision 6 9 19 Revision 6 9 20 Revision 6 9 21 9 22 blank Revision 6 9 23 Revision 6 9 24 Revision 6 9 25 Revision 6 9 26 Revision 6 9 27 Revision 6 9 28 Revision 6 9 29 Revision 6 9 30 Revision 6 9 31 Revision 6 9 32 Revision 6 9 33 Revision 6 9 34 Revision 6 9 35 Revision 6 9 36 Revision 6 9 37 Revision 6 9 38 Revision 6 9 39 Revision 6 9 40 Revision 6 9 41 9 ...

Page 14: ...FAA APPROVED REVISION NUMBER FAA APPROVED REVISION NUMBER PAGE NUMBER 9 47 Revision 6 9 48 Revision 6 9 49 Revision 6 9 50 Revision 6 9 51 Revision 6 9 52 Revision 6 9 53 Revision 6 9 54 Revision 6 9 55 Revision 6 9 56 Revision 6 9 57 5 58 blank Revision 6 9 59 Revision 6 9 60 Revision 6 9 61 Revision 6 9 62 Revision 6 ...

Page 15: ...al 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 Measure U S Gal L U S Gallons to Liters 1 17 Table 1 2 Linear Measure In Cm Inches to Cent...

Page 16: ......

Page 17: ...will be so noted Be 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 Av...

Page 18: ...TC items which are 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 a...

Page 19: ...perator of the aircraft 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 d...

Page 20: ...osen are those with 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...

Page 21: ...ignates 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...

Page 22: ... Battery BLD Bleed 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 G...

Page 23: ...ect IGN Ignitor s 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 Meter...

Page 24: ...unds per Square Inch 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 Ex...

Page 25: ...ages must be put in 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 i...

Page 26: ...e the tail rotor is 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 t...

Page 27: ...ccess to the engine 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 per...

Page 28: ...While contemporary 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...

Page 29: ...m 8 50 ft 2 59 m 30 30 ft 9 23 m 23 00 ft 7 01 M 21 25 6 47 m 15 00 ft 4 57m 6 80 ft 2 07 m DIMENSIONAL CONVERSION ENGLISH FEET METRIC METERS 0 79 4 25 4 57 5 06 6 30 6 80 7 00 7 20 8 20 8 50 15 00 21 25 23 00 26 33 30 30 0 24 1 295 1 393 1 542 1 92 2 07 2 13 2 20 2 50 2 59 4 572 6 477 7 010 8 025 9 235 NOTE ADD 0 63 FOOT 0 19 METER TO ALL VERTICAL DIMENSIONS IF EXTENDED GEAR IS INSTALLED F01 001 ...

Page 30: ... gallons 234 liters 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 ...

Page 31: ...80 160 140 120 100 80 60 40 20 0 200 180 160 140 120 100 80 60 40 20 0 220 240 260 280 300 320 MPH Km H KNOTS F05 002 EXAMPLE CONVERT 100 KNOTS TO MPH AND TO KM HR ENTER 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 Figure 1 2 Speed MPH Knots KmH ...

Page 32: ...PERATURE 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 TEMPERATURE EXAMPLE F C 140 120 100 80 60 40 20 0 20 40 60 60 40 20 0 20 40 60 80 FAHRENHEIT CELCIUS CONVERSIONS F05 003 Figure 1 3 Temperature Conversion Chart ...

Page 33: ...317 98 321 76 325 55 329 33 333 12 336 90 90 340 69 344 47 348 26 352 05 355 83 359 62 363 40 367 19 370 97 374 76 100 378 54 382 33 386 11 389 90 393 69 397 47 401 26 405 04 408 83 412 61 Table 1 2 Linear Measure In Cm Inches to Centimeters 0 1 2 3 4 5 6 7 8 9 Inches Cm Cm Cm Cm Cm Cm Cm Cm Cm Cm 0 2 54 5 08 7 62 10 16 12 70 15 24 17 78 20 32 22 86 10 25 40 27 94 30 48 33 02 35 56 38 10 40 64 43 ...

Page 34: ...346 28 651 28 955 29 260 29 565 29 870 30 174 100 30 479 30 784 31 089 31 394 31 698 32 003 32 308 32 613 32 918 33 222 Table 1 4 Weight Lb Kg Pounds to Kilograms 0 1 2 3 4 5 6 7 8 9 Pounds Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams 0 0 454 0 907 1 361 1 814 2 268 2 722 3 175 3 629 4 082 10 4 536 4 990 5 443 5 897 6 350 6 804 7 257...

Page 35: ...NOTS 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 EXAMPLE 0 5 10 15 20 25 30 35 40 45 50 0 5 10 15 20 25 Figure 1 4 Conversion Chart Knots Meters Second ...

Page 36: ...81 86 23 088 0 7716 8000 0 7860 1 1279 0 850 30 471 752 63 22 225 0 7428 9000 0 7620 1 1456 2 831 26 905 724 29 21 388 0 7148 10000 0 7385 1 1637 4 812 23 338 696 82 20 577 0 6877 11000 0 7155 1 1822 6 793 19 772 670 21 19 791 0 6614 12000 0 6932 1 2011 8 774 16 206 644 40 19 029 0 6360 13000 0 6713 1 2205 10 756 12 640 619 44 18 292 0 6113 14000 0 6500 1 2403 12 737 9 074 595 23 17 577 0 5875 150...

Page 37: ...23 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 38: ...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 flight is proh...

Page 39: ...ÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ 20 40 60 80 100 120 140 0 20 000 18 000 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 0 10 20 30 40 50 60 70 22 000 160 FUEL TEMPERATURE DEGREES F 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...

Page 40: ...RATUIRE FUEL QUANTITY FUEL LOW CAUTION 35 POUNDS 107 C 15 TO 30 C 30 TO 107 C N TACHOMETER 1 59 AND 104 59 TO 104 130 KNOTS 42 TO 130 KNOTS LATER CONFIGURATION 150 75 75 150 50 90 130 150 PSI 107 125 C 30 1 2 3 F MINIMUM OPERATING LIMITS THE EDGE OF A RED LINE IS THE LIMITING VALUE THE POINTER SHOULD NOT ENTER THE RED DURING NORMAL OPERATIONS 50 AND 130 PSI 50 TO 90 PSI 90 TO 130 PSI ENG OIL PRESS...

Page 41: ... 3 7 3 6 Emergency Landing Procedures 3 7 Water Landing 3 7 3 7 Fire 3 9 Engine Fire on the Ground 3 10 Engine Fire During Flight 3 11 Cabin Fire Smoke 3 12 3 8 Engine Fuel Control System Malfunctions 3 14 Fuel Control or Power Turbine governor Failure 3 14 3 9 Other Engine Caution Indications 3 16 Engine Oil Chip Detector 3 16 Low Engine Oil Pressure 3 16 Engine Torque 3 16 3 10 Main Rotor and Ta...

Page 42: ...One Way Lock Failure 3 20 Cyclic Trim Failure 3 21 3 12 Abnormal Vibrations 3 23 3 13 Fuel System Malfunctions 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 28 3 17 Emergency Equip...

Page 43: ...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 44: ...NGINE OUT XMSN OIL PRESS XMSN OIL GEN OUT ENGINE CHIPS M R XMSN CHIPS T R XMSN CHIPS FUEL LOW FUEL FILTER PRESS TO TEST FILTER CLOGGED FILTER CLOGGED TEMP OIL CHIPS LATE CONFIGURATION EARLY CONFIGURATION 1 2 4 3 5 6 7 8 9 10 RED YELLOW RED YELLOW 1 ENGINE OUT 2 TRANSMISSION OIL PRESSURE 3 TRANSMISSION OIL TEMPERATURE 4 GENERATOR OUT 5 ENGINE CHIPS 6 MAIN ROTOR TRANSMISSION CHIPS 7 TAIL ROTOR TRANS...

Page 45: ...55 Procedures Engine Failure In Cruise at 420 Feet AGL or Above F Allison C 18 engine Adjust collective pitch according to altitude and airspeed to maintain rotor speed between 400 and 514 RPM F Allison C 20 engine Adjust collective pitch according to altitude and air speed to maintain rotor speed between 400 and 523 RPM F Apply pedal pressure as necessary to control aircraft yaw F Adjust cyclic c...

Page 46: ...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 F In the eve...

Page 47: ...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 F 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 F If possible fly at...

Page 48: ...ocedures F Close twist grip to cutoff position F 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 F Perform normal e...

Page 49: ...iated with the following Engine Failure Transient rotor droop during large rapid increases in power Governor failure producing an underspeed Procedures F Respond immediately to the low rotor RPM warning by adjusting collec tive to maintain rotor RPM within limits F Check other Caution Warning indicators and engine instruments to con firm engine trouble and respond in accordance with appropriate pr...

Page 50: ...tions Power on Procedures F Descend to hovering altitude over water F Open doors and push door handle full down to prevent relatching F Passengers and copilot exit aircraft F Fly a safe distance away from all personnel in the water to avoid injury F Close twistgrip to the cutoff position and perform a hovering autorotation F Allow aircraft to settle in a level attitude while applying full collecti...

Page 51: ...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 if allowed to contact hot engine exhaust Procedures Cabin Smoke and Fume Elimination...

Page 52: ...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 F If a fire extinguisher is discharged in the cabin use only the amount of extinguishing agent necessary...

Page 53: ...L TO CLOSE F BATTERY EXT PWR switch OFF F Passengers crew EVACUATE If time and situation permit F Rotor brake if installed APPLY F Secure area HAVE PASSENGERS AND SPECTATORS MOVE A SAFE DISTANCE FROM THE AIR CRAFT F Fire extinguisher USE AS APPROPRIATE ENGINE FIRE DURING FLIGHT Conditions At low altitude AGL Procedures F Land immediately POWER ON APPROACH AND LANDING WITHOUT DELAY F Twistgrip CUTO...

Page 54: ... descent to the ground If a power off descent is chosen proceed as follows F Collective DOWN TO ESTABLISH AUTOROTATION TO SELECTED AREA F Twistgrip CUTOFF F Fuel shutoff valve PULL TO CLOSE F Radio MAYDAY CALL F Execute autorotational landing MAINTAIN CONTROL F BATTERY EXT PWR switch OFF F Passengers crew EVACUATE CABIN FIRE SMOKE Conditions On ground Procedures F Twistgrip CUTOFF F BATTERY EXT PW...

Page 55: ... NECESSARY F Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND F BATTERY EXT PWR switch OFF F Passengers crew EVACUATE If unable to land immediately and fire source can be identified F Malfunctioning system OFF F Fire extinguisher USE AS NECESSARY F Cabin VENTILATE F Land AS SOON AS POSSIBLE If fire source is unknown F Cabin heat OFF F GEN OFF F All electrical circuits not required for safety of...

Page 56: ...y increasing Possible right yaw Procedures F Increase collective to load the main rotor simultaneously rolling the twist grip toward the ground idle position until control of N2 speed is obtained F Manually control N2 speed 103 104 with the pilots twistgrip F If operating RPM cannot be controlled close twistgrip to CUTOFF and make an autorotational landing Immediate pilot action is necessary becau...

Page 57: ...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 58: ... OIL CHIPS indicator ON early configuration Conditions Metal contamination of engine main or tail rotor transmission oil Procedures F Land as soon as possible LOW ENGINE OIL PRESSURE Indications Oil pressure decreasing below normal operating range Ref Section II Conditions In flight Procedures F Land as soon as possible F Shut engine down Conditions On ground F Shut engine down ENGINE TORQUE Indic...

Page 59: ...RE Indications Red XMSN OIL PRESS indicator ON late configuration Conditions Transmission oil pressure low Procedures F 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 F Land as soon as possible M R TRANSMISSION CHIP DETECTOR Indications Yellow M R XMSN C...

Page 60: ...n of oil Procedures F 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 F 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 61: ... and power setting Indications Failure is normally indicated by an uncontrollable by pedal yawing to the right Procedures F Reduce power by lowering collective F Adjust airspeed to 50 60 knots F Use left lateral cyclic in combination with collective pitch to limit left sideslip to a reasonable angle F If conditions permit place the twistgrip in the ground idle position once a landing area is selec...

Page 62: ...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 63: ...n 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 F Establish a safe flight condition that produces the least cyclic control force Normally straight and level at the last trimmed airspeed F Actuate the trim switch thru all positions in an attempt to restore trim capability and det...

Page 64: ... 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 F Utilize left hand and legs as necessary to app...

Page 65: ...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 F Turn on start pump F Continue flight If any unusual engine indications or conditions occur land as soon as possible F Turn start pump ON monitor...

Page 66: ...en approximately 35 pounds of fuel remains in fuel tank Procedures F Avoid large steady side slip angles and uncoordinated maneuvers Never use the FUEL LOW light as a working indication of fuel quantity F Land as soon as possible Fuel consumption rates vary with power demand Pilots should land prior to fuel exhaustion Fuel exhaustion will result in engine flameout CAUTION WARNING ...

Page 67: ... switch OFF F Land as soon as possible NOTE No further flights are authorized until battery is inspected and cause of overtemp corrected Indications Yellow BATTERY 140F 160F battery 140 F caution indicator ON Conditions Battery overtemperature at 140 F 60 C Procedures F Battery switch OFF F Battery must remain off line during remainder of flight NOTE The Yellow battery 140 F light will go out afte...

Page 68: ... Check generator GEN circuit breaker IN F Turn the generator GEN switch OFF then ON to reset F 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 F If GEN OUT...

Page 69: ...TALLED Indications Yellow FILTER CLOGGED indicator ON Conditions A predetermined pressure differential has been reached across the engine air inlet Procedures F FILTER BYPASS control handle pull OPEN F SCAV AIR OFF F Service particle separator prior to next flight Ref HMI To prevent compressor erosion avoid operation in a dirty or dusty environment with the filter bypass door open CAUTION ...

Page 70: ...CY EGRESS Pilot compartment doors Pilot doors function as primary and emergency exits Cabin doors Passenger doors function as primary and emergency exits PILOT PASSENGER COMPARTMENT DOOR EXIT TO OPEN TO LOCK EXIT PILOT COMPARTMENT DOOR LH TYPICAL F01 058 CAUTION SAFELOCK INNER HANDLE IN POSITION SHOWN BEFORE FLIGHT Figure 3 2 Emergency Exits ...

Page 71: ...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 72: ......

Page 73: ...ar engine inlet 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 F Oil cooler air inlet CHECK F All inspection panels and cabin doors SECURED F Fuel level cap security CHECK F Engine oil level cap security CHECK NOTE Engine oil level should be checked within 15 minutes...

Page 74: ...indications of bearing failure F F 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 CHECK F F Teeter blades stop to stop Observe four radial molded ridges on each bearing as teetering takes place If ridges assume continuous curved shape bearings are int...

Page 75: ...imum 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 15 per ...

Page 76: ... procedures F F Close twistgrip to the cutoff position F F Use starter to continue motoring engine for at least ten seconds or until TOT decreases below 150 C F Start ignition button release at 58 to 60 percent N1 RELEASE F 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 normal oi...

Page 77: ... Record 6 9 Figure 6 7 Fuel Station JET A at 6 8 Pounds per Gallon Sheet 1 of 2 6 10 Figure 6 7 Fuel Station JET B at 6 5 Pounds per Gallon Sheet 2 of 2 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 Passenger 6 13 6 5 Longitudinal Loading of Cargo 6 14 Exam...

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Page 79: ...ine 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 G...

Page 80: ...6 2 F01 006 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 FORWARD 97 99 104 105 106 LONGITUDINAL TRAVEL INCHES LATERAL TRAVEL INCHES FUSELAGE STATIONS Figure 6 1 Center of Gravity Envelope ...

Page 81: ... 0 ROTOR C STA 100 0 L CARGO COMPARTMENT STA 28 0 STA 174 0 18 1 12 1 2 6 12 1 13 0 CG OF FWD PASSENGER CG OF AFT PASSENGERS CG OF PILOT THREE PLACE COCKPIT STANDARD HE HS STA 73 5 STA 71 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 82: ...01 THRU 0100 ONLY 20 40 60 80 100 120 140 160 180 200 210 240 260 280 300 SLING POINT 3 LEVELING PLUMB STA 92 6 OIL TANK RH SIDE FIREWALL JIG POINT AFT JACKING POINT STA 197 2 STA 174 0 BHD ENGINE SECTION FUEL CELL COMPARTMENT BATTERY STA 78 5 STA 124 0 JIG POINT FWD JACKING POINT STA 96 9 REFERENCE DATUM STA 282 0 f01 061 Figure 6 2 Balance Diagram Sheet 2 of 2 ...

Page 83: ...CSP HE HS 1 Weight and Balance Data ROTORCRAFT FLIGHT MANUAL MD 500 Models 369HE HS HM Revision 6 6 5 f01 062 Figure 6 3 Station Diagram ...

Page 84: ...RCRAFT FLIGHT MANUAL Weight and Balance Data MD 500 Models 369HE HS HM Revision 6 6 6 MDHC MODEL ___________________________ WEIGHT AND BALANCE REPORT F01 063 1 Figure 6 4 Sample Weight and Balance Report Sheet 1 of 2 ...

Page 85: ...CSP HE HS 1 Weight and Balance Data ROTORCRAFT FLIGHT MANUAL MD 500 Models 369HE HS HM Revision 6 6 7 F01 063 2 Figure 6 4 Sample Weight and Balance Report Sheet 2 of 2 ...

Page 86: ...CSP HE HS 1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data MD 500 Models 369HE HS HM Revision 6 6 8 F01 064 Figure 6 5 Sample Surplus and Missing Items ...

Page 87: ...9E BASIC WEIGHT AND BALANCE RECORD CONTINUOUS HISTORY OF CHANGES IN STRUCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE SERIAL NUMBER REGISTRATION NUMBER WEIGHT CHANGE ADDED REMOVED RUNNING TOTAL BASIC AIRCRAFT WEIGHT ARM LONG MOMENT WEIGHT ARM Hughes Helicopters Inc PAGE 4 OF 4 IN LB LONG MOMENT IN LB WEIGHT ARM LONG MOMENT IN LB F01 065 1273 108 36 137840 Figure 6 6 Sample Basic Weight and Balan...

Page 88: ...FUEL QUANTITY IS 422 POUNDS OPTIIONAL SELF SEALING TANKS 1 MAXIMUM FUEL QUANTITY IS 420 5 POUNDS 2 MAXIMUM USABLE FUEL QUANTITY IS 407 5 POUNDS FUEL WT AND CG CURVE USING JET A LONGITUDINAL C G INCHES FUEL QUANTITY GALLONS 65 60 55 50 45 40 35 30 25 20 15 10 5 0 ASTM D 1655 AT 6 8 POUNDS PER GALLON EXAMPLE Find fuel moment for 340 lb fuel 1 Enter chart at 340 lb on fuel weight scale From that poin...

Page 89: ...EL QUANTITY IS 403 5 POUNDS OPTIIONAL SELF SEALING TANKS 1 MAXIMUM FUEL QUANTITY IS 402 POUNDS 2 MAXIMUM USABLE FUEL QUANTITY IS 389 5 POUNDS FUEL WT AND CG CURVE USING JET B LONGITUDINAL C G INCHES FUEL QUANTITY GALLONS 65 60 55 50 45 40 35 30 25 20 15 10 5 0 EXAMPLE Find fuel moment for 340 lb fuel 1 Enter chart at 340 lb on fuel weight scale From that point move to right along the 340 lb line u...

Page 90: ...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 91: ...Utility Stowage Sta 55 20 1 100 20 1 100 Baggage under seat 40 4 400 40 4 400 1 Zero Fuel Weight 2 048 204 320 2 190 217 260 Add Fuel 350 34 000 350 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 369HE Zero Fuel Weight 2 048 99 8 in 369HS Moment at Zero Fuel Weight 217 260 99 2 in 369HS Zero Fuel...

Page 92: ...the 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 forw...

Page 93: ...Fuel Weight 1 978 201 765 2 120 214 705 Add Fuel 400 39 100 400 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 369HE Zero Fuel Weight 1 978 102 1 in 369HS Moment at Zero Fuel Weight 214 705 101 3 in 369HS Zero Fuel Weight 2 120 101 3 in CG Gross Weight 369HE Moment at Gross Weight 240 865 101 3 ...

Page 94: ...xternal 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 gra...

Page 95: ...Cargo 400 2 0 800 400 2 0 800 1 Zero Fuel Weight 1 878 0 58 1 098 2 020 0 54 1 098 Add Fuel 400 0 0 400 0 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 369HE Zero Fuel Weight 1 878 0 58 in 369HS Moment at Zero Fuel Weight 1 098 0 54 in 369HS Zero Fuel Weight 2 020 0 54 in CG Gross Weight 369HE Moment ...

Page 96: ...95 12 155 17 850 180 13 230 12 870 18 900 200 14 700 14 300 21 000 220 16 170 15 730 23 100 240 17 640 17 160 25 200 Baggage Weights and Longitudinal Moments Moment in lb Baggage Weight lb Utility Stowage Compartment Station 52 9 Under Seat and Center Station 110 Behind Seat Station 120 Fwd Bulkhead Station 87 10 529 1 100 1 200 900 20 1 058 2 200 2 400 1 700 30 1 587 3 300 3 600 2 600 40 2 116 4 ...

Page 97: ...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 1 560 2 172 312 1 452 140 1 820 2 534 364 1 694 160 2 080 2 896 416 1 936 170 2 210 3 077 442 2 057 180 2 340 3 258 468 2 178 200 2 600 3 620 520 2 420 220 2 860 3 982 572 2 662 240 3 120 4 344 622 2 904 Baggage Weights and Lateral Moments Baggage Weight lb Station 12 8 ...

Page 98: ...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 99: ...CSP HE HS 1 Weight and Balance Data ROTORCRAFT FLIGHT MANUAL MD 500 Models 369HE HS HM Revision 6 6 21 6 22 blank F01 066 Figure 6 8 Cargo Restraint ...

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Page 101: ...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 13 7 10 Main Rotor Transmission Servicing 7 13 7 11 Tail Rotor Transmission Servicing 7 14 7 12 Cleaning General 7 14 7 13 Cleaning Fuselage Interior Trim and Upholstery 7 14 7 14 Clea...

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Page 103: ...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 104: ... DOOR FORWARD SECTION FLIGHT CONTROLS MAIN ROTOR HORIZONTAL UPPER VERTICAL STABILIZER LOWER VERTICAL STABILIZER TAIL ROTOR TAIL BOOM TAIL ROTOR TRANSMISSION ENGINE MAIN TRANSMISSION POWER TRAIN STABILIZER ENGINE ACCESS DOOR CARGO DOOR LOWER SECTION LANDING GEAR AFT SECTION F01 015 Figure 7 1 Helicopter Major Components ...

Page 105: ... 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 F01 046 Figure 7 2 Ground Handling Wheels ...

Page 106: ...f 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 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 than one blade leng...

Page 107: ...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 108: ... TIEDOWN TETHER MOORING ANCHOR 4 PLACES PITOT TUBE COVER 369H4009 CABLE OR MANILA ROPE ENGINE EXHAUST OUTLET COVER 369H9804 EXTENSION SPRING TO BLADE SOCK TO MOORING ANCHOR TO BLADE SOCK JACK FITTING LOCKPIN FUEL CELL ACCESS DOOR TYPICAL 2 PLACES LOCKPIN STOWAGE FUSELAGE STRUCTURE JACKING FITTING AIR INLET FAIRING COVER 369H9803 ZIPPER ACCESS DOOR LATCH REF TIE CORD F01 048 Figure 7 3 Parking and ...

Page 109: ...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 110: ...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 Hatco Corporation MIL PRF 23699F Series Mobil Jet 254 and Mobil Jet 291 ExxonMobil Lubricants Aeroshell Royco Turbine Oil 560 Royal Lubrican...

Page 111: ...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 1 1 21 31 1 52 U S Oz 45cc 41 51 1 01 U S Oz 30cc Use the materials list...

Page 112: ...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 113: ...K RESERVOIR ENGINE ACCESSORY GEARBOX DRAIN BREATHER FILLER FUEL SUPPLY LINE DRAIN VALVE ENGINE OIL TANK FILLER OIL SYSTEM DRAIN VALVE GROUND RE CEPTACLE FUEL SYSTEM FILLER FUEL CELL S DRAIN VALVE EXTERNAL POWER RE CEPTACLE TAIL ROTOR TRANSMIS SION DRAIN ENGINE WASH FITTING IF INSTALLED MAIN TRANSMISSION SIGHT GAUGE ENGINE OIL SIGHT GAUGE TAIL ROTOR TRANSMISSION SIGHT GAUGE F01 044 Figure 7 4 Servi...

Page 114: ...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 to Alliso...

Page 115: ...until oil level is FULL on sight gauge 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 transmission oil...

Page 116: ... 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 upholstery...

Page 117: ...ith 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 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 surface of plastic rin...

Page 118: ...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 119: ...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 120: ...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 121: ...seconds prior to starter engagement F Motor the engine with the twistgrip in CUTOFF F Release starter switch as necessary to maintain between 5 and 10 N1 speed during the wash rinse F Water injection will continue during coast down until N1 stops F Allow engine to drain F 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...

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Page 123: ...n Strips Installed Takeoff Power Allison 250 C20 8 2 Figure 8 2 Hover Ceiling Vs Temperature OGE Utility Floats Tail Rotor Abrasion Strips Installed Takeoff Power Allison 250 C20 8 3 Figure 8 3 Hover Ceiling Vs Temperature OGE Utility Floats Takeoff Power Allison 250 C20 8 4 Figure 8 4 Hover Ceiling Vs Temperature OGE Takeoff Power Allison 250 C18 8 5 Figure 8 5 Hover Ceiling Vs Temperature OGE Ut...

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Page 125: ...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 126: ...TH 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 2 WT LBS 5 7 5 15 35 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C GROSS WEIGHTS ABOVE 2550 LB MUST BE...

Page 127: ...ITH 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 REDUCE WEIGHT CAPABILITY LBS AS FOLLOWS PRESSURE CABIN HEAT ANTI ICE BOTH 12 000 112 120 236 16 000 20 000 97 83 106 89 206 175 ALT FT SEA LEVEL TO 2 WT LBS 5 7 5 15 35 INCREASE O...

Page 128: ...N 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 2 WT LBS 5 7 5 15 35 INCREASE OR DECREASE WEIGHT CAPABILITY ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C REDUCE WEIGHT CAPABILIT...

Page 129: ...N 3 11 LB WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED OAT C WT 5 15 35 2 5 7 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD GROSS WEIGHTS ABOVE 2550 LB MUST BE EXTERNAL AND JETTISON ABLE ALTITUDE CABIN HEAT ANTI ICE BOTH 10 000 15 000 20 000 125 105 85 155 130 105 290 240 195 REDUCE...

Page 130: ...B WITH ENGINE AIR INLET SCREEN 369H8086 4 50 LB WITH MAIN ROTOR ABRASION TAPE INSTALLED OAT C WT 5 15 35 2 5 7 INCREASE OR DECREASE WEIGHT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD GROSS WEIGHTS ABOVE 2550 LB MUST BE EXTERNAL AND JETTISON ABLE ALTITUDE CABIN HEAT ANTI ICE BOTH 10 000 15 000 20 000 125 105 85 155 130 105 290 240 195 REDUCE WEIGHT ...

Page 131: ...65 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 1570 17000 5182 2155 2090 2020 1935 1850 1750 1635 18000 5486 2070 2005 1935 1850 1770 1675 1560 19000 5791 1990 1920 1850 1775 1690 1605 20000 6096 1905 1845 1775 1700 1615 1530...

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Page 133: ...ti 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 Instructions Engine Air Inlet Deflector 9 21 9 9 Operating Instructions Emergency Floats 9 23 Figure 9 5 Minimum Float Operational Temperature for Over water Flight 9 25...

Page 134: ...keoff and Landing 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 9 61 Figure 9 14 Electrical Controls Console Layout Typical 9 62 Figure 9 15 Cyclic Grip 9 62 ...

Page 135: ...on II Emergency and Malfunction 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 supplemental data for type of optional equipment instal...

Page 136: ...CSP HE HS 1 Heated Pitot Tube 369H90034 369H90115 CSP HE HS 1 Automatic Reignition 369H90118 Section IX Luggage Pod 369H90002 Section IX Litter 369H90011 Section IX Cargo Swing 369H90017 Section IX Cargo Hook 369H90065 369H90072 Section IX Hoist 369H90070 Section IX Utility Floats 369H90086 Section IX Emergency Floats 369H90121 Section IX Searchlight 369H90142 Section IX Anti Ice Fuel Filter 369A9...

Page 137: ...e in flight 5 Compatible if installed 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 assemblie...

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Page 139: ...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 140: ...oad 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 at gross ...

Page 141: ...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 142: ...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 143: ... HM Revision 6 9 9 FAA Approved F01 071 EXTERNAL RELEASE TURN CLOCKWISE ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK LOAD BEAM 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 144: ...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 99 200 199 300 298 400 397 500 497 600 596 700 695 800 794 900 894 1000 993 1100 1092 1200 1191 1300 1291 1400 1390 1500 1490 1600 1589 1700 1688 1800 1...

Page 145: ...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 146: ...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 147: ...eout 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 F 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 F Start pump OFF FILTER ...

Page 148: ...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 149: ...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 151: ...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 152: ...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 153: ...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 skid tube when attaching load to hook with helicopter on ground Apply collective s...

Page 154: ...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 155: ...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 157: ...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 158: ...n 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 is prohib...

Page 159: ...9 5 Operational Temperature Float Inflation Time Altitude Required For Deployment Up to 70 F 21 C 9 0 sec 330 feet Above 70 F 6 3 sec 250 feet 50 40 30 20 10 0 10 20 30 25 0 10 20 30 40 50 60 70 80 90 TEMPERATURE AT TIME OF READING PRESSURE GAUGE F EXAMPLE IF IN A 55 ENVIRONMENT THE GAUGE PRESSURE IS READ AT 3100 PSIG THE MINIMUM FLOAT OPERATIONAL TEMPERATURE IS 5 F PRESSURE PSIG 3000 3100 3200 33...

Page 160: ...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 161: ...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 5 7 10 2 3100 5 9 10 5 3500 6 6 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 162: ...low 99 0 104 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 lb Forward Aft Right Left 2001 to 2250 99 0 104 0 3 0 2000 and below 97 0 104 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...

Page 163: ...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 164: ...ation in 2001 to 2550 99 to 105 5 5 5 0 200 or below 97 to 106 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...

Page 165: ...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 166: ...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 167: ...Weight Pounds Pilot Weight Pounds Passenger Weight 150 175 200 225 Pounds Weight Pounds 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 3...

Page 168: ...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 169: ...s 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 ...

Page 170: ...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 171: ...0 6 000 4 000 2 000 0 60 80 100 INDICATED AIRSPEED KNOTS DENSITY ALTITUDE F01 052 Figure 9 6 Variation of VNE With Altitude VNE WITH BUBBLE DOORS 369H90085 PRESS ALT X 1000 VNE KNOTS IAS C G W UP TO 2536 LBS C OAT 0 1 4 7 10 13 30 104 86 167 15 113 95 76 58 0 104 85 67 49 15 95 77 59 30 111 105 87 68 50 45 103 97 79 61 369H6528 511 Figure 9 7 VNE Placard ...

Page 172: ...he 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 ...

Page 173: ... 500 Models 369HE HS HM Revision 6 9 39 FAA Approved 0 20 40 60 10 30 50 70 0 4000 8000 12000 16000 2000 6000 10000 14000 18000 CORRECTED FOR INSTRUMENT ERROR 2000 LB OR LESS MORE THAN 2000 LB INDICATED AIRSPEED F01 051 DENSITY ALTITUDE FEET Figure 9 8 Best Rate of Climb Speed ...

Page 174: ...L MD 500 Models 369HE HS HM CSP HE HS 1 Revision 6 9 40 FAA Approved 0 20 40 60 80 100 120 10 30 50 70 90 110 INDICATED AIRSPEED KNOTS 0 20 40 60 80 100 120 10 30 50 70 90 110 CALIBRATED AIRSPEED KNOTS F01 050 Figure 9 9 Indicated Airspeed Vs Calibrated Airspeed ...

Page 175: ...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...

Page 176: ......

Page 177: ... 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 178: ...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 179: ...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 180: ... 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 181: ...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 182: ... HE HS 1 Revision 6 9 48 FAA Approved 22 000 20 000 18 000 16 000 14 000 12 000 10 000 8 000 6 000 4 000 2 000 0 0 10 20 30 10 20 30 40 50 0 20 40 60 20 40 TEMPERATURE DEGREES C TEMPERATURE DEGREES F PRESSURE ALTITUDE FEET F01 054 Figure 9 10 Takeoff and Landing Limitations 250 C18 Engine ...

Page 183: ...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 184: ...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 185: ...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 186: ...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 187: ...H AND INDICATOR PANEL EARLY INSTRUMENT PANEL WITH LATER MODIFIED AUTO REIGNITION SYSTEM SWITCH AND INDICATOR PNEL RE IGN ARMED PRESS TO RESET OFF AUTO REIGN ARM RE IGN ARMED PRESS TO RESET OFF AUTO REIGN TEST LATER INSTRUMENT PANEL EARLY UNMODIFIED AUTO REIGNITION SWITCH AND INDICATOR PANEL NOTE SHOWN WITH SWITCH GUARD REMOVED NOTE SHOWN WITH SWITCH GUARD REMOVED LATER MODIFIED AUTO REIGNITION SWI...

Page 188: ...ncrease engine torque pressure to approximately 40 psi Press and release RE IGN light Light should go out F 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 illuminate indicating that the ignition igniter is firing If RE IGN light is reset OFF at than 40 psi torque it wi...

Page 189: ...ating that the ignition igniter has been energized F If it is desired to extinguish the RE IGN light press and release RE IGN light Light should go out F 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 rpm warning system is activated main rotor speeds below 98 percent N2...

Page 190: ...ndicators illuminate and the sound of the igniter firing is heard F Release test switch Only the RE IGN light should remain illuminated after the test switch is released F 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 Whenever there ...

Page 191: ...reignition system is armed under all operating conditions Failure or deactivation of the engine failure low rotor rpm warning system renders the reignition system inoperative Under certain failure conditions the ARMED light may stay on Pulling out the ENG OUT circuit breaker will disarm the Auto Reignition system Following any activation of reignition system caused by flameout from snow ice or wat...

Page 192: ......

Page 193: ...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 194: ...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 F01 080 1 2 3 4 5 6 7 8 9 10 11 12 13 14 1 DC GENERATOR GENERATOR OUT 2 ENGINE CHIPS 3 T...

Page 195: ...HS 1 Optional Equipment 369HM Configuration ROTORCRAFT FLIGHT MANUAL MD 500 Models 369HE HS HM Revision 6 9 61 FAA Approved PART IV NORMAL PROCEDURES F01 078 Figure 9 13 Type T Instrument Panel Layout Typical ...

Page 196: ...S 1 Revision 6 9 62 FAA Approved F01 079 CIRCUIT BREAKER PANEL PILOT S COLLECTIVE ASH TRAY AND LIGHTER SWITCH CONTROL PANEL LIGHTS CONTROL PANEL Figure 9 14 Electrical Controls Console Layout Typical CYCLIC TRIM DWN UP L R CARGO HOOK RELEASE HOIST GUILLOTINE FLOATS INFLATION Figure 9 15 Cyclic Grip ...

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