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CSP–520N–1

MD 520N (500N) ROTORCRAFT FLIGHT MANUAL

TM

F–iii/(F–iv blank)

Original

APPROVING AUTHORITIES

Centro Técnico Aeroespacial (CTA)

This Rotorcraft Flight Manual is approved by the FAA on behalf of Centro Técnico Aeroes-
pacial for Brazilian registered rotorcrafts in accordance with the ‘‘Regulamentos Brasileiros
de Homologação Aeronáutica’’ (RBHA) Part 21, Section 21.29.

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Summary of Contents for MD520N

Page 1: ...THIS IS A COMPLETE REPRINT OF CSP 520N 1 AND IS CURRENT THROUGH REISSUE 1 INCLUDING REVISIONS 1 AND 2...

Page 2: ......

Page 3: ...F05 000 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 _________________ MD 520N Cover R...

Page 4: ......

Page 5: ...IONAL LIMITATIONS FROM SECTION IX AS A RESULT OF AN INSTALLED OPTIONAL EQUIPMENT ITEM SECTIONS III IV AND V CONTAIN RECOMMENDED PROCEDURES AND DATA AND ARE FAA APPROVED THE AIRWORTHINESS LIMITATIONS L...

Page 6: ...25 June 1992 Revision 3 28 July 1992 Revision 4 17 September 1992 Revision 5 29 April 1993 Revision 6 8 September 1993 Revision 7 3 May 1994 Revision 8 7 February 1995 Revision 9 17 July 1995 Revisio...

Page 7: ...OVING AUTHORITIES Centro T cnico Aeroespacial CTA This Rotorcraft Flight Manual is approved by the FAA on behalf of Centro T cnico Aeroes pacial for Brazilian registered rotorcrafts in accordance with...

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Page 9: ...n 1 4 1 8 Definition of Terms 1 4 1 9 Abbreviations 1 5 1 10 Technical Publications 1 7 1 11 Design and Construction 1 9 1 12 Electrical System 1 12 1 13 Auto Reignition System 1 13 1 14 Capacities an...

Page 10: ...l System Malfunctions 3 14 3 9 Other Engine Caution Indications 3 16 3 10 Main Rotor and Aft Transmission Malfunctions 3 17 3 11 Flight Control Malfunctions 3 18 3 12 Abnormal Vibrations 3 23 3 13 Fue...

Page 11: ...imb 5 6 5 6 Height Velocity Diagram Gross Weight Limits For Height velocity diagram 5 8 5 7 Hover Ceiling Vs Gross Weight 5 11 5 8 Power Check Chart Allison 250 C20R 2 5 20 Section VI Weight and Balan...

Page 12: ...ransparent Plastic 7 16 7 15 Fluid Leak Analysis 7 16 7 16 Preservation and Storage 7 17 7 17 Flyable Storage No Time Limit 7 17 7 18 Cockpit Door Removal and Installation 7 18 7 19 Special Operationa...

Page 13: ...t Paragraph 2 10 Updated fuel specification designations and added alternate fuels Section III Paragraph 3 9 Added malfunctions procedures for low engine oil pressure and loss of torque indication Par...

Page 14: ...Revision 2 F iii F iv blank Original F v Original F vi Revision 2 F vii Revision 1 F viii Revision 2 F ix Revision 2 F x Revision 2 F xi Revision 2 F xii Revision 2 F xiii Revision 2 F xiv Revision 2...

Page 15: ...1 16 Original 1 17 Original 1 18 Original 1 19 Original 1 20 Original 1 21 Original 1 22 Original II 2 i 2 ii blank Revision 2 2 1 Original 2 2 Original 2 3 Original 2 4 Original 2 5 Revision 2 2 6 Re...

Page 16: ...4 Original 3 5 Original 3 6 Original 3 7 Original 3 8 Original 3 9 Original 3 10 Original 3 11 Original 3 12 Original 3 13 Original 3 14 Original 3 15 Original 3 16 Revision 2 3 17 Revision 2 3 18 Rev...

Page 17: ...7 Original 4 8 Original 4 9 Original 4 10 Original 4 11 Original 4 12 Original 4 13 Revision 2 4 14 Original 4 15 Revision 2 4 16 Revision 1 4 17 Original 4 18 Original 4 19 Original 4 20 Original 4...

Page 18: ...inal 5 9 Original 5 10 Original 5 11 Original 5 12 Original 5 13 Original 5 14 Original 5 15 Original 5 16 Original 5 17 Original 5 18 Original 5 19 Original 5 20 Original 5 21 5 22 blank Original 5 2...

Page 19: ...nal 6 18 Original 6 19 Original 6 20 Original 6 21 6 22 blank Original VII 7 i 7 ii blank Revision 2 7 1 Original 7 2 Original 7 3 Original 7 4 Original 7 5 Original 7 6 Original 7 7 Revision 2 7 8 Re...

Page 20: ...8 i 8 ii blank Original 8 1 8 2 blank Original IX 9 i Original 9 ii Original 9 1 Revision 1 9 2 Original 9 3 Original 9 4 Original 9 5 Original 9 6 Original 9 7 Original 9 8 Original 9 9 Original 9 10...

Page 21: ...1 13 1 14 Capacities and Dimensions 1 14 Table 1 1 Fuel System Standard Non Self Sealing Fuel Tanks 1 14 Table 1 2 Fuel System Optional Self Sealing Fuel Tanks 1 14 Figure 1 1 MD 520N Principal Dimens...

Page 22: ......

Page 23: ...d by the Federal Aviation Administration under FAA Type Certificate Number H3WE Certification of the aircraft has been accomplished in accordance with all appli cable United States Department of Trans...

Page 24: ...ffective Pages By referring to the Log of Revisions By Date the pilot may review a chro nological listing of changes to the Flight Manual Reading the Summary of Revisions will inform the pilot of what...

Page 25: ...are the original weight and balance report and equipment list equipment both required and optional installed on the aircraft at the time of licensing SECTION VII AIRCRAFT HANDLING SERVICING AND MAINT...

Page 26: ...cular operation A black change bar l in the page margin designates the latest new or changed information appearing on that page A hand points to changes in the contents of an illustration 1 8 DEFINITI...

Page 27: ...COM Communication CCW Counter Clockwise CW Clockwise D dBA Decibel A weighted DC Direct Current DIR Direction Directional E EGT Exhaust Gas Temperature ENG Engine EXT Extend External F F Fahrenheit F...

Page 28: ...CP Maximum continuous power MDHI MD Helicopters Inc Min Minutes MPH Miles Per Hour N N1 Gas Producer Speed N2 Power Turbine Speed NAV Navigation NR Rotor Speed O OAT Outside Air Temperature OGE Out of...

Page 29: ...flight manual content as appropriate To ensure that MDHI manuals continue to show current changes revised information is supplied as follows Revisions Change to parts of the manual by the replacement...

Page 30: ...ctural Repair Manual SRM Illustrated Parts Catalog IPC Service Information Notices and Letters New and revised publications are available through MDHS Subscription Ser vice Further information may be...

Page 31: ...f a pilot compartment and di rectly aft separated by a bulkhead a passenger cargo compartment The pi lot compartment is equipped with seats for the pilot and either one or two passengers A canopy of t...

Page 32: ...the forward compartment for pilot and passen gers The two aft doors allow entry to the passenger cargo compartment Transparent tinted windows are contained in the doors Powerplant The power plant used...

Page 33: ...alities In forward flight the vertical stabilizers in conjunction with the direct jet thruster provide the required anti torque and directional control Main rotor system The helicopter utilizes a five...

Page 34: ...e ENGINE OUT low rotor audio warning This early ge neric version was delivered on aircraft serial numbers LN001 through LN044 On aircraft serial numbers LN045 and subsequent a modified late generic ve...

Page 35: ...d This light will remain ON until manually reset after N1 and NR in crease back above the values 55 N1 453 NR that activate the ENGINE OUT low rotor warning NOTE In the event of a NR or N1 tach genera...

Page 36: ...7 2 1 6 1 9 12 5 5 7 Total 242 53 3 64 0 416 0 188 7 Table 1 2 Fuel System Optional Self Sealing Fuel Tanks Fuel Type Liters Imp Gal U S Gal Pounds Kilograms Jet A Usable 226 8 49 9 59 9 407 0 184 9...

Page 37: ...8 8 ft 2 3m 7 7 ft 0 4m 1 4 ft 9 6m 31 39 ft 7 6m 24 9 ft 2 1m 6 9 ft 2 3m 7 7 ft NOTES 1 HELICOPTER ON GROUND WITH FULL FUEL TYPICAL ATTITUDE OF CARGO DECK 4 7 DEGREES NOSE UP 2 IF EXTENDED LANDING...

Page 38: ...0 140 120 100 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 F03 003 EXAMPLE CONVERT 100 KNOTS TO MPH AND TO KM HR ENTER CHART AT 100 KNOTS AND FOLLOW ARROW...

Page 39: ...ERATURE 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...

Page 40: ...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 61 110 416 40 420 18 423 97 427 75 431 54 435 62 439 11 44...

Page 41: ...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 6 Weight Pounds to Kilograms 0 1 2 3 4 5 6 7 8 9 Pounds Kilo grams Kilo grams K...

Page 42: ...VERT 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 E...

Page 43: ...29 1 29 0 28 9 28 7 28 6 28 5 28 4 28 3 28 2 28 1 28 0 28 8 1055 1050 1045 1040 1035 EXAMPLE 1 29 44 IN HG 997 MBAR EXAMPLE 2 30 18 IN HG 1022 MBAR 1035 1030 1025 1020 1015 1010 1005 1000 IN Hg 30 6...

Page 44: ...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...

Page 45: ...haft N2 Limits 2 6 2 8 Electrical System Limitations 2 6 2 9 Starter Limitations 2 7 2 10 Fuel System Limitations 2 7 Table 2 1 Unusable Fuel Standard Non Self Sealing Fuel Tanks 2 8 Table 2 2 Unusabl...

Page 46: ......

Page 47: ...tification is based on an Engine Failure Warning System including both visual and audio indications Low Rotor Warning System Outside Air Tem perature gauge and Fuel Low caution light being installed a...

Page 48: ...0 000 feet Ambient temperature limitations From sea level to 6000 feet pressure altitude the maximum engine air inlet ambient temperature is 54 C 130 F from 6000 feet to 20 000 feet pressure altitude...

Page 49: ...eight in the utility stowage compartment is 50 pounds CG Limits Ensure helicopter CG and weight are within approved limits throughout flight Ref Figure 2 1 1 2 3 4 1 2 3 4 5 5 98 99 100 102 104 106 10...

Page 50: ...ing The rotor brake may be applied after engine shutdown with the rotor at or be low 195 RPM 2 6 ROTOR RPM SPEED LIMITATIONS Normal Operating Range 473 RPM to 477 RPM 99 100 percent N2 Power on maximu...

Page 51: ...et Temperature limits Maximum takeoff 5 minute 810 C Maximum continuous 752 C Maximum for starting lightoff 150 C Transient limits During start and shutdown 810 C and above for 10 seconds or less with...

Page 52: ...ure 2 2 Maximum Allowable Output Shaft N2 Limits Engine oil system limits Flight operation temperature limits 0 C to 107 C Flight operation pressure limits 50 to 130 psi with the following minimums 12...

Page 53: ...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...

Page 54: ...s Jet A 7 9 1 7 2 1 14 3 6 5 Jet B 7 9 1 7 2 1 13 6 6 2 Cold weather operations Fuels must meet anti icing capability of JP 4 when operating at 4 C 40 F or less The 250 C20R 2 SP engine does not requi...

Page 55: ...UEL PUMP ON 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 HI...

Page 56: ...MAL OPERATIONS YELLOW YELLOW INDICATES CAUTIONARY OPERATING RANGE GREEN GREEN INDICATES NORMAL OPERATING RANGE 150 AMPS 85 TO 150 AMPS 0 TO 85 AMPS FUEL LOW CAUTION 35 POUNDS 12 5 POUNDS AMMETER 50 AN...

Page 57: ...60 TO 752 C 843 C TURBINE OUTLET TEMPERATURE ANALOG DIGITAL ANALOG 400 TO 752 C 752 TO 810 C 810 C 899 C 927 C 150 C Max TOT for Lightoff F05 008 2 0 1 2 3 4 5 N2 RPM 99 AND 100 99 TO 100 106 5 ROTOR...

Page 58: ...and Pres sure Altitude columns cross Refer to example 1 107 KIAS 4 Autorotation VNE Refer to example 1 5 is determined by subtracting 21 knots from the powered flight VNE until in example 1 90 knots...

Page 59: ...12 111 123 C 134 123 11 2 5 5 123 128 VNE C 30 20 10 0 10 20 30 40 45 OAT PRESS ALT X 1000 0 137 145 2 132 140 147 4 128 135 141 148 150 149 147 6 123 130 136 142 148 148 135 124 119 FOR AUTOROTATION...

Page 60: ...16 100 86 FOR AUTOROTATION VNE REDUCE SPEED BY 21 KTS 87K MIN DO NOT EXCEED CHART VNE MAX VNE 129 KTS WITH LESS THAN 35 LB FUEL VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2201 TO 2350 LB C 0 2 4 6 8...

Page 61: ...9 99 84 72 FOR AUTOROTATION VNE REDUCE SPEED BY 21 KTS 90K MIN DO NOT EXCEED CHART VNE MAX VNE 129 KTS WITH LESS THAN 35 LB FUEL VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2501 TO 2650 LB C 0 2 4 6 8...

Page 62: ...0 59 FOR AUTOROTATION VNE REDUCE SPEED BY 21 KTS 94K MIN DO NOT EXCEED CHART VNE MAX VNE 129 KTS WITH LESS THAN 35 LB FUEL VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2851 TO 3100 LB C 0 2 4 6 8 10 12...

Page 63: ...8 88 73 60 48 38 20 145 140 135 130 121 97 81 67 54 43 10 147 141 136 108 88 73 61 49 38 0 148 121 97 81 67 55 44 10 150 140 108 89 74 61 50 39 20 123 98 82 68 56 45 30 144 111 90 76 63 51 41 40 126 1...

Page 64: ...COMPLIANCE WITH 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 i...

Page 65: ...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...

Page 66: ...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...

Page 67: ...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...

Page 68: ...9 10 11 12 13 14 16 BAT 140o XMSN OIL TEMP REIGN ENGINE OUT BAT 160o 3 ALT P RST F F XMSN OIL PRESS FUEL LEVEL LOW M R XMSN CHIPS AIR FRAME FILTER AIR FLTR CLOGD AFT XMSN CHIPS 15 FLOAT P TEST LH RH...

Page 69: ...tors are actuated when N1 falls below 55 or NR falls below 453 NR Ref 95 1 N2 Procedures Engine Failure In Cruise at 500 Feet AGL or Above F Adjust collective pitch according to altitude and airspeed...

Page 70: ...loss of power time and altitude permitting place twistgrip in cutoff and close fuel shutoff valve F Select landing area and maneuver as required F If operating at reduced rotor RPM to extend glide or...

Page 71: ...hich the power loss occurs F As the ground is approached flare as required to reduce forward speed and rate of descent F Touch down in a level attitude increasing collective pitch to cushion land ing...

Page 72: ...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...

Page 73: ...ases 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...

Page 74: ...wer 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...

Page 75: ...of electrical 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 person...

Page 76: ...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 b...

Page 77: ...UATE 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 FI...

Page 78: ...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 MA...

Page 79: ...ARY F Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND F BAT EXT switch OFF F Passengers crew EVACUATE IF UNABLE TO LAND IMMEDIATELY AND FIRE SOURCE CAN BE IDENTIFIED F Malfunctioning system OFF F...

Page 80: ...sing 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 c...

Page 81: ...ght or a power on decent make an au torotational landing Conditions Power Turbine Governor Surge Indications N2 fluctuating governor not maintaining pre set speed 99 100 N2 Procedures NOTE Turning the...

Page 82: ...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 Condition...

Page 83: ...soon as possible M R TRANSMISSION OIL TEMPERATURE Indications Red XMSN OIL TEMP indicator ON Conditions Transmission oil temperature exceeds maximum limit Procedures F Land as soon as possible M R TR...

Page 84: ...e fan to stop turning resulting in a complete loss of fan thrust Directional control becomes dependant on airspeed and power setting Indications Failure is normally indicated by an uncontrollable yawi...

Page 85: ...autorotation Conditions Anti torque failure fixed thruster setting right pedal applied Procedures F Adjust power to maintain 50 to 60 knots airspeed F Use a shallow approach and running landing touch...

Page 86: ...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...

Page 87: ...ued 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 tha...

Page 88: ...itudinal 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 fai...

Page 89: ...til the cause of the vibration has been identified and corrected 3 13 FUEL SYSTEM MALFUNCTIONS FUEL FILTER Indications Yellow FUEL FILTER indicator ON Conditions A predetermined pressure differential...

Page 90: ...l quantity Procedures F Avoid large steady side slip angles and uncoordinated maneuvers Sideslips may cause fuel starvation and result in unexpected power loss or engine failure Avoid large steady sid...

Page 91: ...m the DC electrical bus when battery temperature reaches 160 F F Land as soon as possible NOTE No further flights are authorized until battery is inspected and cause of overtemp corrected Indications...

Page 92: ...not powering electrical bus Procedures F Check generator GEN circuit breaker IN and return generator switch to ON if tripped OFF F Turn the generator switch OFF then ON to reset F If GEN OUT indicato...

Page 93: ...TALLED Indications Yellow AIR FILTER CLOGGED indicator ON Conditions A predetermined pressure differential has been reached across the engine air inlet Procedures F FILTER BYPASS control handle OPEN F...

Page 94: ...ENT DOOR EXIT TO OPEN TO LOCK EXIT PILOT COMPARTMENT DOOR LH TYPICAL F03 012 Figure 3 2 Emergency Exits 3 17 EMERGENCY EQUIPMENT First Aid Kit The first aid kit is located on the right side forward ed...

Page 95: ...9 Figure 4 3 Cyclic and Collective Stick Grips 4 10 4 2 Engine Pre Start Cockpit Check 4 11 4 3 Engine Start 4 14 4 4 Engine Run Up 4 16 4 5 Before Takeoff 4 19 4 6 Takeoff 4 21 4 7 Cruise 4 22 4 8 Lo...

Page 96: ......

Page 97: ...ence 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...

Page 98: ...CSP 520N 1 MD 520N 500N ROTORCRAFT FLIGHT MANUAL Normal Procedures R Original 4 2 FAA Approved F05 010 1 2 3 4 5 7 8 6 3 INTERIOR EXTERIOR Figure 4 1 Pilot s Preflight Guide...

Page 99: ...may occur if air is allowed to enter the fuel system EXTERIOR FUSELAGE FORWARD END F Aircraft tiedowns and covers REMOVED F Aircraft attitude for weak or damaged landing gear dampers CHECK F Canopy fo...

Page 100: ...Aft transmission oil level CHECK F Engine air inlet plenum chamber NO OBSTRUCTIONS OR FOREIGN OBJECTS If helicopter has been standing in falling snow clear engine inlet area and surrounding skin area...

Page 101: ...lower NO OBSTRUCTIONS NO DAMAGE F Position and anti collision lights CHECK F Horizontal stabilizer CHECK F Vertical stabilizers CHECK F F YSAS CHECK AS DESIRED REF PARAGRAPH 4 16 F Direct jet thruste...

Page 102: ...Engine electrical connections CHECK F Generator control unit circuit breakers 2 CHECK F Fuel control N2 governor and associated linkages CHECK F Exhaust ducts CHECK F Engine compartment doors for con...

Page 103: ...ccess panels SECURED F Controls access panel SECURED F Loose equipment or cargo SECURED NOTE Refer to Paragraph 4 10 if planning doors off flight F Seats seat belts and shoulder harness CHECK F Compar...

Page 104: ...cks prior to subsequent flights of the same day F Fluid levels CHECK F Engine compartment fluid leaks and bypass indicators CHECK F Air inlet screens particle separator CHECK F Fuel cap access doors a...

Page 105: ...E OUTLET AMMETER CLOCK N1 TACHOMETER TORQUE INDICATOR FRESH AIR VENT FUEL SHUTOFF VALVE QUANTITY INDICATOR EDGE LIGHTED SWITCH PANEL LATE GENERIC EARLY GENERIC F05 011C DUAL TACHOMETER ANTI ICE SWITCH...

Page 106: ...RICTION NUT TWIST GRIP LANDING LIGHT SWITCH GOVERNOR INCREASE DECREASE SWITCH COPILOT S SWITCH HOUSING CARGO HOOK CYCLIC TRIM DWN R L UP RELEASE OPTION COPILOT S COLLECTIVE OPTIONAL ICS COMM TRIGGER P...

Page 107: ...on of shoulder harness inertia lock CHECK F Cyclic collective friction off and pedals CHECK FULL TRAVEL F Cyclic stick NEUTRAL FRICTION ON NOTE Cyclic stick longitudinal neutral position is about 35 p...

Page 108: ...EXT for external power start AS REQUIRED F F If used connect GPU NOTE Minimum capacity 20V dc with 500 amp load Maximum capacity 28 5V dc with 500 amp load F Lights AS REQUIRED F Key switch ON F Engi...

Page 109: ...truments CHECK NOTE If analog digital TOT indicator is installed verify power ON by noting an appropriate digital display indication F XMSN OIL PRESS ENG OUT and GEN warning caution lights ON F Press...

Page 110: ...onfiguration Only F Start pump AS REQUIRED NOTE Start pump required when using alternate or emergency fuel Ref to Section II F Rotors CLEARED F Start ignition button PRESS AND HOLD NOTE Starter time l...

Page 111: ...grip 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 Eng...

Page 112: ...ignition Check is performed prior to flying into falling or blowing snow F Electrical power SELECT F F BAT EXT switch SELECT BAT F F External power start DISCONNECT GPU F Set generator GEN to ON GEN O...

Page 113: ...smission oil pressure the auto reignition system is armed F Press reignition RE IGN P RST light LAMP OUT F N2 high beep range 103 or more do not exceed 104 CHECK F N2 low beep range 94 or less CHECK F...

Page 114: ...system may be checked by verifying that the flapper door scavenge air outlet is open THROTTLE RIGGING CHECK NOTE If the flight will involve rolling the twistgrip to the ground idle position while air...

Page 115: ...ol friction RELEASE AND SET AS DESIRED When removing collective friction be alert for abnormal collective loads that would cause the collective to raise by itself F Cyclic response check F F With coll...

Page 116: ...e performed at the pilot s discretion F F Prior to takeoff F F F While on the ground at 98 N2 place RE IGN test switch in the FLT middle position RE IGN and ENGINE OUT lights should illuminate F F F B...

Page 117: ...should occur during flight a precautionary landing should be made No further flights shall be attempted until the cause of the vibration has been identified and corrected NOTE Momentary fluctuation i...

Page 118: ...ted turns maneuvers may cause fuel starvation with less than 35 pounds of fuel on board F Controllability during downwind hovering sideward and rearward flight has been demonstrated to be adequate in...

Page 119: ...shing autorotation to prevent rotor overspeed if flight is at high gross weight or high density altitude To re duce rate of descent or to extend gliding distance operate at minimum rotor rpm Restore R...

Page 120: ...4 10 DOORS OFF FLIGHT Doors off flight is permitted in accordance with the restrictions noted in Sec tion II Any object that is not properly secured may exit the aircraft during flight Items secured w...

Page 121: ...ION ON F Cyclic stick neutral position approximately 1 3 from full aft TRIM TO NEUTRAL APPLY FRICTION F All unnecessary bleed air and electrical equipment OFF F Pedals NEUTRAL F Twistgrip from GROUND...

Page 122: ...enerator switch OFF F YSAS AS DESIRED F NAV COM switches OFF F All other switches OFF F Rotor brake if installed apply at 195 rpm or less release during last rotor revolution APPLY Care should be take...

Page 123: ...N ON F Stabilize N2 at exactly 100 percent BEEP as required for 15 seconds SET F Pilot s twistgrip SNAP TO IDLE Begin time check with stop watch Stop time as N1 passes through 65 per cent Observe elap...

Page 124: ...he trailing edge of the horizontal stabilizer so the fingers of your right hand rest on both sides of the trailing edge of the right vertical stabilator With your left hand shake the helicopter latera...

Page 125: ...icopter Takeoff Takeoff using maximum takeoff power at the speed for best rate of climb Ref Section V Proceed away from noise sensitive areas If takeoff must be made over noise sensitive area distance...

Page 126: ......

Page 127: ...S Gross Weight IGE 3 Foot Skid Clearance Short Landing Gear Standard Engine Inlet Takeoff Power 5 12 Figure 5 7 Hover Ceiling VS Gross Weight IGE 3 Foot Skid Clearance Extended Landing Gear Standard E...

Page 128: ...nal 5 ii FAA Approved PARAGRAPH PAGE Figure 5 13 Hover Ceiling VS Gross Weight Out of Ground Effect Engine Air Particle Separator Inlet Takeoff Power 5 19 5 8 Power Check Chart Allison 250 C20R 2 5 20...

Page 129: ...TICS NOTE No determination has been made by the Federal Aviation Administration that the noise levels in this manual are or should be acceptable or unacceptable for operation at into or out of any air...

Page 130: ...airspeed CAS Use of Chart Use the chart as illustrated by the example To determine calibrated air speed the pilot must know the indicated airspeed Example WANTED Calibrated airspeed KNOWN Indicated ai...

Page 131: ...ROTORCRAFT FLIGHT MANUAL TM Original 5 3 FAA Approved 30 40 50 60 70 80 90 100 110 120 130 140 150 160 50 60 70 80 90 100 110 120 130 140 150 30 40 INDICATED AIRSPEED KTS CALIBRATED AIRSPEED KTS F05 0...

Page 132: ...of chart with known or estimated OAT move up to known pressure altitude line move to left and note densi ty altitude Pressure altitude is found by setting 29 92 1013 mb in kolsman window altimeter err...

Page 133: ...10 8 6 4 2 0 2 40 30 20 10 0 10 20 30 40 1 36 1 34 1 32 1 30 1 28 1 26 1 24 1 22 1 20 1 18 1 16 1 14 1 12 1 10 1 08 1 06 1 04 1 02 1 00 TEMPERATURE DEGREES C 40 30 20 10 0 10 20 30 40 50 60 70 80 90 1...

Page 134: ...ed 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 11 000 feet M...

Page 135: ...0N 500N ROTORCRAFT FLIGHT MANUAL TM Original 5 7 FAA Approved 20000 18000 16000 14000 12000 10000 8000 6000 4000 2000 0 0 20 40 60 80 100 DENSITY ALTITUDE FEET INDICATED AIRSPEED KNOTS F05 015A Figure...

Page 136: ...hin the cross hatched area is not prohibited but should be avoided The recommended takeoff profile line shows the airspeed altitude combina tions recommended for takeoff The unmarked region represents...

Page 137: ...L TM Original 5 9 FAA Approved 20 40 60 80 100 120 140 0 100 200 300 400 500 INDICATED AIRSPEED KNOTS SMOOTH HARD SURFACE WIND CALM AVOID OPERATION IN CROSS HATCHED AREA 0 ALTITUDE AGL FEET RECOMMENDE...

Page 138: ...OTORCRAFT FLIGHT MANUAL TM Original 5 10 FAA Approved 14000 12000 10000 8000 6000 4000 2000 0 DENSITY ALTITUDE FEET GROSS WEIGHT POUNDS 2200 2400 2600 2800 3000 3200 3400 3600 F05 017 Figure 5 5 Gross...

Page 139: ...rward flight has been demonstrated to be adequate in winds up to 17 knots NOTE Momentary excursions into the transient TOT torque power ranges may occur when hovering in a right crosswind at higher de...

Page 140: ...VE AND JETTISONABLE 3350 LBS MUST BE EXTERNAL PRESSURE CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349 296 252 665 612 518 438 ALT FT REDUCE WEIGHT CAPABILITY lbs AS FOLLO...

Page 141: ...518 438 ALT FT REDUCE WEIGHT CAPABILITY lbs AS FOLLOWS APPLICABLE TO ALL TEMPERATURES MAXIMUM INTERNAL GROSS WEIGHT GROSS WEIGHTS ABOVE AND JETTISONABLE 3350 LBS MUST BE EXTERNAL THIS CHART BASED ON...

Page 142: ...BLE 3350 LBS MUST BE EXTERNAL PRESSURE CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349 296 252 665 612 518 438 ALT FT REDUCE WEIGHT CAPABILITY lbs AS FOLLOWS APPLICABLE TO...

Page 143: ...ERNAL GROSS WEIGHT GROSS WEIGHTS ABOVE AND JETTISONABLE 3350 LBS MUST BE EXTERNAL PRESSURE CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349 296 252 665 612 518 438 ALT FT A...

Page 144: ...TOR AND SCAV AIR ON 3 70 LBS WITH MIST ELIMINATOR AND SCAV AIR OFF 2 180 LBS WITH MIST ELIMINATOR AND SCAV AIR ON PRESSURE CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349...

Page 145: ...ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349 296 252 665 612 518 438 ALT FT REDUCE WEIGHT CAPABILITY lbs AS FOLLOWS APPLICABLE TO ALL TEMPERATURES 3 70 LBS WITH MIST ELIMINATOR AND SC...

Page 146: ...LBS WITH MIST ELIMINATOR AND SCAV AIR OFF 2 180 LBS WITH MIST ELIMINATOR AND SCAV AIR ON PRESSURE CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 295 282 239 203 368 349 296 252 665 612 518 438...

Page 147: ...ST STACKS WITH REDUCE WEIGHT 1 110 LBS WITHOUT MIST ELIMINATOR AND SCAV AIR ON 3 70 LBS WITH MIST ELIMINATOR AND SCAV AIR OFF 2 180 LBS WITH MIST ELIMINATOR AND SCAV AIR ON PRESSURE ALT FT CABIN HEAT...

Page 148: ...ator is installed subtract 8 C from the TOT read during flight before comparing it with the specification TOT If a standard engine air inlet is installed add 14 C to the TOT read during flight before...

Page 149: ...e obtained Example 2 WANTED Check engine performance DATA OBTAINED DURING HOVERING Torque 42 0 psig TOT 650 C PA 8000 feet OAT 7 5 C NOTE Be sure to add 2 5 C to the observed OAT before continuing Spe...

Page 150: ......

Page 151: ...lank FAA Approved 500 525 550 575 600 625 650 675 700 725 750 775 800 TURBINE OUTLET TEMPERATURE C 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 105 500 475 450 425 400 375 350 325 300 275 250 225...

Page 152: ......

Page 153: ...Surplus and Missing Items 6 7 Figure 6 5 Sample Weight and Balance Record 6 8 6 2 Weight and Balance Criteria 6 9 6 3 Equipment Removal or Installation 6 9 6 4 Weight and Balance Determination Passen...

Page 154: ......

Page 155: ...115 pounds per square foot Utility Stowage Compartment Limited to 50 pounds Center of Gravity Limits Lateral is right of centerline lateral is left of centerline when look ing forward Table 6 1 Center...

Page 156: ...0 102 104 106 108 110 3 2300 2500 2700 2900 3100 3300 GROSS WEIGHT POUNDS LONGITUDINAL ARM INCHES FORWARD CG LIMIT 2100 1900 1700 101 4 107 771 kg 1796 815 kg 1497 kg 1406 kg 1315 kg 1134 kg 1043 kg 1...

Page 157: ...5 5 13 0 STA 73 5 STA 100 0 STA 78 5 CG OF PILOT CG OF COPILOT CARGO COMPARTMENT STA 124 0 ROTOR C L 0 0 12 2 12 2 STA 105 0 0 8 168 8 PASSENGER STA 71 5 CG OF CENTER PASSENGER NOTE REFERENCE COORDINA...

Page 158: ...TA 168 20 STA 124 75 CANT STA 129 0 STA 132 9 STA 137 50 STA 146 62 STA 155 75 STA 174 00 WL 34 50 WL 13 10 JACKING POINT STA 96 89 BL 25 6 WL 0 00 C BEAM L WL 32 00 WL 11 98 WL 38 36 WL 14 19 WL 0 00...

Page 159: ...G PLUMB STA 92 6 REFERENCE DATUM STA 78 5 JIG POINT FWD JACKING POINT STA 96 9 ENGINE SECTION FUEL CELL COMPARTMENT JIG POINT AFT JACKING POINT STA 275 4 124 0 OIL TANK RH SIDE FIRE WALL NOTE IN LEVEL...

Page 160: ...WEIGHT 100 1 INCHES EXAMPLE 2 AFT WEIGHT LBS LONG ARM IN LONG MOMENT IN LB BASIC WEIGHT 1704 6 113 6 193721 PILOT 170 0 73 5 12495 PASSENGER AFT L H 170 0 105 0 17850 PASSENGER AFT R H 170 0 105 0 17...

Page 161: ...12 6 I C S W O HEADSETS 1 2 35 5 0 9 43 1 ATTITUDE GYRO IND 3 3 42 2 0 0 139 0 DIRECTIONAL GYRO IND 2 7 42 6 0 0 115 0 INST VERT SPEED IND 1 7 45 0 3 5 77 6 VHF COMM 369D24164 7 0 55 0 0 8 385 6 VHF N...

Page 162: ...Weight and Balance Data CSP 520N 1 MD 520N 500N ROTORCRAFT FLIGHT MANUAL TM Original 6 8 Figure 6 5 Sample Weight and Balance Record...

Page 163: ...nal 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 Deter...

Page 164: ...R H 170 17 850 Passenger Aft L H 170 17 850 Utility Stowage Station 52 9 20 1058 Baggage under seat 40 4 400 1 Zero Fuel Weight Add Fuel Jet A 6 8 Lbs Gal 2 445 422 259 869 41229 2 Gross Weight 2 867...

Page 165: ...l be within 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 loc...

Page 166: ...ot 170 12 495 Passenger Fwd Outboard 170 12 495 Cargo 1000 100 000 1 Zero Fuel Weight Add Fuel Jet A 3 045 150 318 711 14160 2 Gross Weight 3 195 332 871 Calculation of Longitudinal CG CG Zero Fuel We...

Page 167: ...l loadings are permissible if gross weight longitudinal and lateral center of gravity considerations permit For crew and passenger lateral center of gravity see Figure 6 2 6 7 LATERAL LOADING OF CARGO...

Page 168: ...392 Pilot L H 170 13 0 2 210 PassengerJ JFwdJ R H 170 15 5 2 635 Cargo 1000 2 0 2 000 1 Zero Fuel Weight Add Fuel Jet A 3 045 150 0 7 0 2 033 0 2 Gross Weight 3 195 0 6 2 033 Calculation of Lateral CG...

Page 169: ...Y 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 QUANTI...

Page 170: ...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...

Page 171: ...1 760 11 440 16 800 170 12 495 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 Baggage Moment...

Page 172: ...H Station 13 0 Passenger R H Fwd Station 15 5 Passenger Center Fwd Station 0 8 Aft Passenger R H and L H Station 12 2 120 1 560 1 860 96 1 464 140 1 820 2 170 112 1 708 160 2 080 2 480 128 1 952 170 2...

Page 173: ...al 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...

Page 174: ...OOP FOR VERTICAL AND LATERAL RESTRAINT VIEW SHOWING LOCATION OF CARGO TIEDOWN POINTS AND LOOPS MINIMUM LOOP STRINGTH 1800 LB WRAP CONTAINER WITH SIMILAR STRAP SUCH THAT LOOPS CANNOT SLIP VIEW II CARGO...

Page 175: ...eral 7 7 Table 7 1 Servicing Materials Operating Supplies 7 7 Figure 7 4 Servicing Points Sheet 1 of 2 7 11 Figure 7 4 Servicing Points Sheet 2 of 2 7 12 7 8 Fuel System Servicing 7 13 7 9 Engine Oil...

Page 176: ......

Page 177: ...ge rating may be used Engine starting requirements are approximately 375 amperes mini mum Before connecting external power be sure that helicopter main electrical power selector switch is OFF After po...

Page 178: ...20N 500N ROTORCRAFT FLIGHT MANUAL R Original 7 2 FAA Approved STATOR SAS CONTROL ACTUATOR ENGINE ASSY W EXTENDED DEFLECTORS ENGINE ASSY W O EXTENDED DEFLECTORS F05 038 Figure 7 1 MD 500N Helicopter Ma...

Page 179: ...nd for towing helicopter Ref Figure 7 2 At regular intervals check that wheel tire pressure is a maximum of 80 to 90 psi F05 041 WARNING BE SURE LOCK SNAPS INTO POSITION SHOWN BEFORE RELEASING JACK HA...

Page 180: ...Manually move helicopter on ground handling wheels by balancing at tail boom and pushing on rear fuselage portion of air frame Towing Tow helicopter on ground handling wheels by attaching suitable to...

Page 181: ...rectly above tailboom Ref Figure 7 3 Install blade socks on all blades Secure blade sock tiedown cord for blade located above tailboom to tailboom Secure other blade sock tiedown cords to fuselage jac...

Page 182: ...INE AIR INLET FAIRING COVER INSTALLATION JACK FITTING INSTALLATION TYPICAL 2 PLACES TO BLADE SOCK TO MOORING ANCHOR TO BLADE SOCK JACK FITTING LOCKPIN PITOT TUBE COVER INSTALLATION PITOT TUBE COVER FU...

Page 183: ...S Pt 5 67 liters Mobil SHC 626 or the materials listed under Item 4 3 Main Transmission 369F5100 Capacity 14 0 US Pt 6 62 liters Use Mobil SHC 626 only 4 Engine Capacity 3 0 US Qt 2 84 liters Ambient...

Page 184: ...Box 518 East 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 Ameri...

Page 185: ...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 a...

Page 186: ...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 requirem...

Page 187: ...PER FUEL SYSTEM FILLER ENGNE OIL TANK FILLER FUEL CELL DRAIN VALVE AFT TRANSMISSION ENGINE ACCESSORY GEARBOX DRAIN FILLER LIQUID LEVEL SIGHT GAGE OVERBOARD OIL DRAIN LINE ENGINE COMBUSTION FUEL DRAIN...

Page 188: ...F05 043 2 ENGINE OIL TANK DRAIN ENGINE OIL COOLER DRAIN STATION 137 50 BULKHEAD MAIN TRANSMISSION OIL COOLER DRAIN ENGINE WASH FITTING SCAVENGE OIL FILTER OIL FILTER BYPASS INDICATOR ENGINE FUEL FILTE...

Page 189: ...contain anti ice additive which conforms to MIL 1 27686 or later These fuels do not require additional anti ice addi tive Cold weather fuel mixtures To assure consistent starts at temperatures at or...

Page 190: ...e oil system Make certain that oil tank filler cap is secured after servicing 7 10 MAIN ROTOR AND AFT TRANSMISSION SERVICING Main rotor transmission Check transmission oil level at liquid level sight...

Page 191: ...and or leave residue that can result in corrosion Examples of cleaning agents that are not to be used are Fantastic and 409 type cleaners or locally made strong soap cleaners 7 12 CLEANING FUSELAGE I...

Page 192: ...by rinsing with clean water and rubbing light ly with palm of hand Use mild soap and water solution or aircraft type plastic cleaner to remove oil spots and similar residue Never attempt to dry plast...

Page 193: ...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 instal...

Page 194: ...vers and equipment used to park and moor helicopter Perform daily preflight check Ref Section IV 7 18 COCKPIT DOOR REMOVAL AND INSTALLATION Door removal Open door Remove interior cover plates pilot s...

Page 195: ...IGHT MANUAL R Revision 2 7 19 FAA Approved DOOR FRAME PILOT S DOOR DOOR STRUCTURE DOOR HINGE FUSELAGE STRUCTURE HINGE PIN TAB F60 043 PASSENGER CARGO COMPARTMENT DOOR LH SHOWN RH SIMILAR Figure 7 5 Pi...

Page 196: ...tarter generator can be used to motor the Allison 250 Series en gine for compressor cleaning cycle Input voltage should be 24 vdc but it is permissible to use 12 vdc To prevent starter generator damag...

Page 197: ...tarter 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 duri...

Page 198: ......

Page 199: ...and Performance Data CSP 520N 1 MD 520N 500N ROTORCRAFT FLIGHT MANUAL TM Original 8 i 8 ii blank SECTION VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA TABLE OF CONTENTS PARAGRAPH PAGE 8 1 ICAO Nois...

Page 200: ......

Page 201: ...rements and were obtained by using approved analysis techniques and approved data from actual noise tests Model MD500N Engine Allison 250 C20R 2 Gross Weight 3350 lbs Configuration VH KTAS Level Flyov...

Page 202: ......

Page 203: ...y Model 500N Helicopter 9 2 9 4 Optional Equipment Performance Data 9 2 9 5 Operating Instructions Cargo Hook Kit 9 3 Figure 9 1 Center of Gravity Envelope 9 4 Figure 9 2 VNE Placards External Load Op...

Page 204: ......

Page 205: ...gency 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...

Page 206: ...III where appropri ate 9 3 COMPATIBILITY COMBINED OPTIONAL EQUIPMENT Table 9 2 Optional Equipment Kit Compatibility Model 500N Helicopter Compatibility Blank Yes X No Optional Equipment Part Number A...

Page 207: ...00 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...

Page 208: ...binations operating gross weight 3850 pounds FAR 133 Center of Gravity Limitations 98 99 100 102 104 106 108 110 3 2300 2500 2700 2900 3100 3300 GROSS WEIGHT POUNDS LONGITUDINAL ARM INCHES FORWARD CG...

Page 209: ...With no load on hook airspeed limits are unchanged With load on hook airspeed limits are presented on the exterior load VNE placards NOTE Use caution as size and shape of load and load attaching cable...

Page 210: ...tating External Load Limit 2000 Pounds installed on or next to cargo hook VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 3200 OR LESS C 0 2 4 6 8 10 12 14 16 30 69 20 59 10 69 0 79 60 10 71 20 62 30 73 5...

Page 211: ...cal release handle to release cargo in the event of an elec trical failure Operate handle quickly and deliberately Ref Figure 9 3 NOTE Ground support personnel should manually assure positive reset of...

Page 212: ...ical and emergency operation of cargo hook release Ref Figure 9 3 Check operation of external release knob located on left side of cargo hook body HookDshouldDreturnDtoDtheDclosedDpositionDafterDabove...

Page 213: ...L TM Original 9 9 FAA Approved EXTERNAL RELEASE TURN CLOCKWISE ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK LOAD BEAM Figure 9 4 Cargo Hook PART V PERFORMANCE DATA Refer to Section V for I...

Page 214: ...Data 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 Cargo Longitudinal CG 99 3 Cargo Weight lb Moment 10...

Page 215: ...te the requirement for use of fuel containing anti ice additives The anti ice airframe fuel filter incorporates a filter unit mounted in series between the aircraft fuel system and the engine fuel sys...

Page 216: ...ON PROCEDURES ANTI ICE AIRFRAME FUEL FILTER Indications Yellow FRAME FILTER AIR caution indicator ON Conditions Anti ice airframe fuel filter becoming clogged with ice or other solid contaminants Proc...

Page 217: ...cur if air is allowed to enter the fuel system Drain any residual water in the filter unit through the drain valve on the bottom of the filter unit NOTE If aircraft has been exposed to freezing temper...

Page 218: ...uipment Anti Ice Airframe Fuel FIlter CSP 520N 1 MD 520N 500N ROTORCRAFT FLIGHT MANUAL TM Original 9 14 FAA Approved FILTER BOWL FIREWALL TEST BUTTON ANTI ICE DRAIN VALVE Figure 9 5 Anti Ice Airframe...

Page 219: ...circuits for each float This indi cator is located on the caution and warning indicator panel The circuit break er is located at the bottom of the circuit breaker panel A recessed switch is provided...

Page 220: ...ght is 25 F 31 7 C minimum 117 F 47 C maximum Altitude limits floats inflated For water and ground landings change of altitude is limited to 6500 feet below the altitude at inflation or to 6500 feet b...

Page 221: ...nds at Station 102 7 to 1949 pounds at Station 106 8 Placards When emergency floats are installed the following placards are required Placard 1 Placard 2 WARNING FLOAT INFLATION ABOVE 81 KNOTS IAS AT...

Page 222: ...NE Placard PART III EMERGENCY AND MALFUNCTION PROCEDURES EMERGENCY FLOAT INFLATION If emergency occurs at airspeeds greater than maximum permissible float inflation speed i e 81 knots IAS at less than...

Page 223: ...h Minimize forward speed prior to water contact Recommended water contact speed 10 knots or less Do not lower collective until forward speed is 5 knots or less Landings have been dem onstrated at gros...

Page 224: ...tery EXT when using an external power source Check FLOATS circuit breaker IN Press to test green float FLOAT P TEST LH RH indicator LH and RH indicator lamps should illuminate indicating that each cir...

Page 225: ...IGHT HAND SKID LEFT HAND SIMILAR Figure 9 7 Float Pressure Gauge PART V PERFORMANCE DATA Hover Performance with Stowed Floats No change from that of the basic helicopter with extended landing gear PAR...

Page 226: ......

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