MD Helicopters MD900 with PW206E Flight Manual Download

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CSP–900RFM206E–1

ROTORCRAFT FLIGHT MANUAL

MD900 With PW 206E

Original

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Summary of Contents for MD900 with PW206E

Page 1: ...ls MD900 with PW 206E Helicopter Original FILING INSTRUCTIONS This manual replaces CSP 900ERFM 1 in its entirety Remove all pages in CSP 900ERFM 1 do not remove actual weight and balance record in Sec...

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Page 3: ...CSP 900RFM206E 1 Model MD900 with PW206E F90 001 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 _________________ Cover...

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Page 5: ...IONS 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 X as a result of an installed op...

Page 6: ...Original Issue 3 September 1999 Revision 1 02 November 2001 Revision 2 18 September 2002 Reissue 1 3 March 2003 This reissue replaces CSP 900ERFM 1 in its entirety Approved By________________________...

Page 7: ...CSP 900RFM206E 1 ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E Original F iii F iv blank APPROVING AUTHORITIES...

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Page 9: ...tation 1 3 1 5 Definition of Terms 1 3 1 6 Abbreviations 1 4 1 7 Multi Purpose Utility Operations 1 7 1 8 Technical Publications 1 7 1 9 Rotorcraft Certification 1 9 1 10 Pilot s Briefing 1 9 1 11 Dim...

Page 10: ...Aircraft Shutdown Manual 3 15 3 8 Fire Emergencies 3 16 3 9 Flight Control Malfunctions 3 20 3 10 Pitot Static System Malfunction Single or Dual Pitot Tube Installation 3 24 3 11 Engine and Generator...

Page 11: ...speed Calibration 5 4 5 5 Best Rate of Climb Speed 5 6 5 6 Rate of Climb and Descent OEI 5 8 5 7 Rate of Climb AEO 5 22 5 8 Hover Ceiling AEO 5 37 5 9 Hover Ceiling OEI 5 46 5 10 Height Velocity Diagr...

Page 12: ...11 Fuel System 7 30 7 12 Electrical System 7 33 7 13 Environmental Control 7 36 7 14 Integrated Instrumentation Display System IIDS 7 38 7 15 IIDS Data Storage 7 46 7 16 Balance Monitoring System 7 4...

Page 13: ...quipment Performance Data 10 2 10 5 Operating Instructions Air Conditioning P N 900P7250302 101 10 3 10 6 Operating Instructions Controllable Landing Search Light 10 7 10 7 Operating Instructions Roto...

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Page 15: ...ire Emergencies Paragraph 3 9 Revised anti torque failure procedures Paragraph 3 11 Added note regarding high engine oil temperatures Added information to Generator Failure regarding the ESNTL pow3 er...

Page 16: ...nal F v Original F vi Original F vii Original F viii Original F ix F x blank Original F xi Original F xii Original F xiii Original F xiv Original F xv Original F xvi Original F xvii Original F xviii O...

Page 17: ...11 Original 1 12 Original 1 13 Original 1 14 Original 1 15 Original 1 16 Original 1 17 Original 1 18 Original II 2 i Original 2 ii Original 2 1 Original 2 2 Original 2 3 Original 2 4 Original 2 5 Ori...

Page 18: ...l 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 Original 3 17 Original 3 18 Original 3 19 Original 3 20 Original 3 21...

Page 19: ...iginal 3 41 Original 3 42 Original IV 4 i 4 ii blank Original 4 1 Original 4 2 Original 4 3 Original 4 4 Original 4 5 Original 4 6 Original 4 7 Original 4 8 Original 4 9 Original 4 10 Original 4 11 Or...

Page 20: ...Original 4 31 Original 4 32 Original 4 33 4 34 blank Original V 5 i Original 5 ii Original 5 iii 5 iv blank Original 5 1 Original 5 2 Original 5 3 Original 5 4 Original 5 5 Original 5 6 Original 5 7 O...

Page 21: ...nal 5 28 Original 5 29 Original 5 30 Original 5 31 Original 5 32 Original 5 33 Original 5 34 Original 5 35 Original 5 36 Original 5 37 Original 5 38 Original 5 39 Original 5 40 Original 5 41 Original...

Page 22: ...al 6 1 Original 6 2 Original 6 3 Original 6 4 Original 6 5 Original 6 6 Original 6 7 Original 6 8 Original 6 9 Original 6 10 Original 6 11 Original 6 12 Original 6 13 Original 6 14 Original 6 15 Origi...

Page 23: ...riginal 7 9 Original 7 10 Original 7 11 Original 7 12 Original 7 13 Original 7 14 Original 7 15 Original 7 16 Original 7 17 Original 7 18 Original 7 19 Original 7 20 Original 7 21 Original 7 22 Origin...

Page 24: ...ginal 7 42 Original 7 43 Original 7 44 Original 7 45 Original 7 46 Original 7 47 Original 7 48 Original 7 49 Original 7 50 Original 7 51 Original 7 52 Original 7 53 Original 7 54 Original 7 55 Origina...

Page 25: ...8 2 Original 8 3 Original 8 4 Original 8 5 Original 8 6 Original 8 7 Original 8 8 Original 8 9 Original 8 10 Original 8 11 Original 8 12 Original 8 13 Original 8 14 Original 8 15 Original 8 16 Origin...

Page 26: ...8 35 Original 8 36 Original 8 37 Original 8 38 Original 8 39 Original 8 40 Original 8 41 Original 8 42 Original 8 43 Original 8 44 Original 8 45 Original 8 46 Original IX 9 i 9 ii blank Original 9 1...

Page 27: ...iginal 9 21 Original 9 22 Original 9 23 Original 9 24 Original 9 25 Original 9 26 Original X 10 i Original 10 ii Original 10 1 Original 10 2 Original 10 3 Original 10 4 Original 10 5 Original 10 6 Ori...

Page 28: ...al 10 29 Original 10 30 Original 10 31 Original 10 32 Original 10 33 10 34 blank Original 10 35 Original 10 36 Original 10 37 Original 10 38 Original 10 39 Original 10 40 Original 10 41 Original 10 42...

Page 29: ...T FLIGHT MANUAL MD900 With PW 206E Original F xxv F xxvi blank LIST OF EFFECTIVE PAGES SECTION NON FAA APPROVED REVISION NUMBER FAA APPROVED REVISION NUMBER PAGE NUMBER 11 7 Original 11 8 Original 11...

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Page 31: ...riefing 1 9 1 11 Dimensions 1 10 Figure 1 1 MD Explorer Rotorcraft Principal Dimensions 1 10 Figure 1 2 Interior Dimensions and Volumes 1 11 1 12 Conversion Charts and Tables 1 12 Figure 1 3 Speed MPH...

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Page 33: ...Revisions and the List of Effective Pages By referring to the Log of Revisions By Date the pilot may review a chronological listing of changes to the Flight Manual Reading the Summary of Revisions wi...

Page 34: ...pment list equipment both required and optional installed on the aircraft at the time of licensing SECTION VII SYSTEMS DESCRIPTION Offers a pilot oriented technical description of the operation of eac...

Page 35: ...changes in the contents of an illustration A WARNING brings to the pilot s immediate attention that equipment damage and or personal injury will occur if the instruction is disregarded placed after th...

Page 36: ...l to or greater than Less than Equal to or less than A AC Air Conditioner A N Alphanumeric AGL Above Ground Level ALT Alternate Altitude AOG Aircraft On Ground APU Auxiliary Power Unit ASCM Aircraft S...

Page 37: ...ty Altitude Hg Mercury HIRF High Intensity Radiated Field HP Pressure Altitude HSI Horizontal Situation Indicator Hot Section Inspection HVR Hover HYD Hydraulic I IAS Indicated Airspeed ICS Intercom S...

Page 38: ...ngine Inoperative OGE Out of Ground Effect OVRD Override OVSP Overspeed P PLA Power Lever Angle PMA Permanent Magnet Alternator PNL Panel POSN Position PRI Primary Pt Pint R R Right REL Release RET Re...

Page 39: ...ORER may be installed and used 1 8 TECHNICAL PUBLICATIONS A file of technical publications is available to aid in obtaining maximum utilization of your rotorcraft Revisions and new issue publications...

Page 40: ...publications are available Rotorcraft Flight Manual RFM Rotorcraft Maintenance Manual RMM Servicing and Maintenance Instruments Electrical Avionics Component Maintenance Manual CMM Structural Repair...

Page 41: ...istration under FAA Type Certificate Number H19NM The FAA model designation is MD900 The FAA ICAO aircraft type designator is EXPL The MD Helicopters Inc commercial designation is MD Explorer 1 10 PIL...

Page 42: ...Figure 1 2 for exterior dimensions and interior volumes F92 002A 5 33 FT 38 38 FT 5 0 9 17 FT STATIC GROUND LINE DESIGN GROSS WEIGHT 3 16 32 33 FT 12 00 FT 10 92 FT 9 33 FT 7 33 FT 33 83 FT 1 62 M 5 9...

Page 43: ...ral Original 1 11 4 08 FT 1 2 M 4 16 FT 1 2 M WITH DOOR ON 4 33 FT 1 3 M WITH DOOR OFF ENTIRE AFT CABIN 172 5 FT3 4 9 M3 BAGGAGE COMPARTMENT 51 4 FT3 1 5 M3 4 75 FT 1 4 M 18 25 FT 5 5 M 12 9 FT 3 9 M...

Page 44: ...20 0 180 160 140 120 100 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 EXAMPLE CONVERT 100 KNOTS TO MPH AND TO KM HR ENTER CHART AT 100 KNOTS AND FOLLOW A...

Page 45: ...TEMPERATURE 50 F METHOD ENTER AT 50 F READ 10 C ACROSS ON C SCALE METHOD MAY BE REVERSED TO FIND F WHEN C IS KNOWN ALTERNATE METHOD F 9 5 X C 32 C 5 9 F 32 TEMPERATURE EXAMPLE F C 140 120 100 80 60 40...

Page 46: ...8 321 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...

Page 47: ...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 Pounds to Kilograms 0 1 2 3 4 5 6 7 8 9 Pounds Kilo grams Kilo gra...

Page 48: ...S 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 KN...

Page 49: ...LIBARS 1000 995 990 985 980 975 970 965 960 955 950 945 29 5 29 4 29 3 29 2 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 1035 1030 1025 1020 1015 1010 1005 1000...

Page 50: ...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...

Page 51: ...Envelope 2 5 Figure 2 5 Center of Gravity Envelope 2 5 2 6 Rotor Brake Limitations 2 5 2 7 Rotor Speed Limitations 2 6 2 8 Transmission Limitations 2 6 2 9 Power Plant Limitations 2 6 2 10 Generator L...

Page 52: ...AFT FLIGHT MANUAL MD900 With PW 206E Limitations CSP 900RFM206E 1 FAA Approved Original 2 ii PARAGRAPH PAGE Figure 2 14 Decals and Placards Sheet 1 of 2 2 13 Figure 2 14 Decals and Placards Sheet 2 of...

Page 53: ...s opened or removed is approved under the following conditions Baggage door removed With the baggage door removed and cockpit and cabin doors closed maximum airspeed is limited to the 140 KIAS envelop...

Page 54: ...000 16000 14000 12000 10000 8000 6000 4000 2000 0 30 40 50 PRESSURE ALTITUDE FEET FREE AIR TEMPERATURE C 36 PRIMARY FUELS ONLY PRIMARY AND SECONDARY FUELS Figure 2 1 Ambient Temperature Envelope IIDS...

Page 55: ...ENSITY ALTITUDE FEET 120 135 270 190 80 A CONTROLLABILITY ENVELOPE FOR CROSSWIND CONDITIONS F92 009 15300 15 KTS 17 KTS 17 KTS CRITICAL AZIMUTH B B HOVER IGE OPERATION POSSIBLE IN CALM WINDS OR WINDS...

Page 56: ...ET INDICATED AIRSPEED KNOTS 30 C 36 C F92 010 VNE AUTOROTATION OEI OPERATIONS HYDRAULICS FAILURE VSCS FAILURE XMSN CHIP LIGHT 100 KIAS ENVELOPE 140 KIAS ENVELOPE 5100 LB VNE POWER ON VNE 25 C 5100 625...

Page 57: ...VITY CG ENVELOPE Ensure helicopter CG and weight are within approved limits throughout flight F92 011 194 196 198 200 202 204 206 7000 6500 6000 5500 5000 4500 4000 3500 3000 FUSELAGE STATION IN WEIGH...

Page 58: ...il pressure See Figure 2 1 1 Maximum transmission oil temperature 110 C Minimum transmission oil temperature 18 C 2 9 POWER PLANT LIMITATIONS Any time a limit is exceeded the exceeded limit shall be r...

Page 59: ...nsient limits 101 to 108 for 20 seconds not cumulative NG limitations Normal limits Maximum continuous 98 7 Transient limits 98 8 to 103 4 for 20 seconds OEI operating limits Maximum continuous 100 4...

Page 60: ...he altitude temperature envelope Ref Figure 2 1 Notes 2 Using these secondary fuels the engine shall operate satisfactorily up to 10 000 FT Ref Figure 2 1 Additional fuel specifications may be found i...

Page 61: ...DS NP NR EEC MAN FAIL NP EEC MAN FAIL ENG OUT TORQUE ENGINE TORQUE EXHAUST GAS TEMPERATURE DISPLAY POWER TURBINE SPEED DISPLAY ROTOR SPEED DISPLAY DISPLAY F92 012 DIGITAL DISPLAYS EGT Figure 2 6 Prima...

Page 62: ...14 NOTE GREATER THAN LESS THAN EEC MAN FAIL TORQUE OEI OPERATIONS 130 124 122 EEC MAN FAIL TORQUE NORMAL OPERATIONS Figure 2 8 Engine Torque ENG OUT EGT ENG OUT EGT OEI OPERATION F92 015 863 C 820 C 8...

Page 63: ...AY FUEL QUANTITY ENGINE OIL ENGINE OIL PRESSURE DISPLAY GENERATOR LOAD DISPLAY GAS PRODUCER TURBINE SPEED DISPLAY TEMPERATURE DISPLAY PRESSURE DISPLAY TRANSMISSION OIL TRANSMISSION OIL TEMPERATURE DIS...

Page 64: ...TION 75 PSI NONE LOW WARNING 65 PSI 50 PSI LOW CAUTION 300 LBS LOW FUEL WARNING SEGMENT 150 LBS F92E 018 FLIGHT RIGHT LOW FUEL WARNING TICK MARK 97 TO 127 LBS IDLE NOTE GREATER THAN LESS THAN Figure 2...

Page 65: ...AGE COMPARTMENT FLOOR NO ARTICLES TO BE STOWED UNDER SEATS LOCATED ON COCKPIT DOOR LOWER WINDOW FRAME 1 LOCATED ON UPPER COCKPIT DOOR FRAME 2 LOCATED ADJACENT TO COCKPIT DOOR ACCESS HANDLE PRIOR TO FL...

Page 66: ...EP USEABLE CAP 158 5 U S GALS WITH RANGE EXTENDER INSTALLED LOCATED ABOVE FUEL FILLER LOCATED ABOVE FUEL FILLER LOCATED ON RANGE EXTENDER FILLER LOCATED ON RANGE EXTENDER FILLER LOCATED ABOVE STATIC P...

Page 67: ...Engine Failure 3 6 Water Landing OEI AEO 3 7 3 5 EEC Malfunctions 3 9 Figure 3 1 EEC Caution Warning Annunciators 3 9 EEC Critical Fault 3 9 EEC Non Critical Fault 3 10 EEC Manual Control 3 12 3 6 Eng...

Page 68: ...ngine High Oil Pressure 3 26 Engine Low Oil Pressure 3 26 Engine Chips 3 27 NG High 3 27 NG Low 3 27 Generator High Load 3 28 Generator 3 28 3 12 Transmission Malfunction Indications 3 29 Figure 3 6 T...

Page 69: ...8 Baggage Door 3 38 IIDS 3 39 3 15 Other Malfunction Advisories 3 39 IIDS Failure 3 39 Battery Discharge 3 39 Extinguisher Pressure Low 3 40 IPS Bypass 3 40 NACA Inlet Malfunction 3 40 Rotor Speed Dis...

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Page 71: ...ssengers aircraft or personnel on the ground These procedures are recommended to minimize danger to the helicopter However these procedures should not limit the pilot from taking additional actions if...

Page 72: ...on The following logic applies to the warning advisories 1 ENG OUT FIRE CAB HEAT and LOW FUEL warning tick mark flash only go OFF if condition that caused the warning goes away 2 All other warnings tu...

Page 73: ...le The ENG OUT advisory is disabled with aircraft on the ground SINGLE ENGINE FAILURE Indications ENG OUT annunciator illuminated and low rotor tone on for one cycle Affected engine torque NP and NG d...

Page 74: ...w armed NOTE If attempting a restart leave fuel shutoff valve ON Do not attempt restart if a malfunction is suspected F Land as soon as practical NOTE If cabin heat or air conditioning is being used w...

Page 75: ...NP and NG decreasing to zero Procedures F Lower collective and maintain rotor speed within limits F Perform autorotation to suitable landing area LOW ROTOR RPM WARNING Procedures F Adjust collective a...

Page 76: ...ened when airspeed is 60 KIAS or less F Make autorotative approach flaring as required to minimize forward speed at touchdown F Level aircraft Increase collective pitch as contact is made with the wat...

Page 77: ...own at approximately 40 KIAS F At approximately 50 FT enter a decelerating attitude and increase power to reduce rate of closure F Descend to hovering altitude over water F Passengers and copilot exit...

Page 78: ...ately 40 KIAS F At approximately 50 FT enter a decelerating attitude and increase power to reduce rate of closure F As water contact is made shut down engine and hold the helicopter as level as possib...

Page 79: ...ycles In the event that the EEC on one of the engines fails the fuel flow of that engine remains fixed and can only be controlled by the twistgrip The engine with the serviceable EEC will attempt to m...

Page 80: ...t using a combination of collective and twistgrips EEC NON CRITICAL FAULT An EEC caution annunciator ON in flight may result in one of the following indica tions Indications Engine torque matching may...

Page 81: ...Continue flight F After landing perform manual engine shutdown Ref paragraph 3 7 Conditions On ground Procedures F Perform manual engine shutdown Ref paragraph 3 7 Indications NP and NR indications n...

Page 82: ...rmal automatic start Flight with one EEC failed one engine manually controlled should be considered an abnormal procedure It should only be done to evacuate the helicopter from a hazardous environment...

Page 83: ...ne ROTATE TO FULL OPEN PAST THE NORMAL DETENT THIS RESETS THE PLA F F Twist grip on selected engine ROTATE TO OFF NOTE AT a point between NORMAL and OFF the twist grip will no longer be able to be rot...

Page 84: ...rotate twistgrip toward normal until lightoff occurs Observe EGT indication for immediate temperature rise Monitor EGT and NG during start Increase twistgrip toward normal only as necessary to keep NG...

Page 85: ...can no longer be rotated toward the OFF position without applying additional force approximately 30 to 40 LBS F Utility panel F F All unnecessary bleed air and electrical equipment OFF F Fuel system...

Page 86: ...talled APPLY F Power switch OFF Conditions In flight Procedures F Cabin heat OFF if source of smoke is the cabin heat duct F Fresh air vents OPEN F AC VENT switch VENT LOW OR VENT HIGH NOTE If crew st...

Page 87: ...F Engine control switches OFF F Passengers crew EVACUATE F Rotor brake if installed APPLY F Power switch OFF Conditions In flight Procedures F Cabin heat OFF F Fresh air vents OPEN F Generator switch...

Page 88: ...ine Transmission Deck Fire Annunciators ENGINE FIRE ON GROUND Indications Engine FIRE warning annunciator ON and activation of the warning tone for two cycles Procedures F Engine control switches OFF...

Page 89: ...harge switch if installed PRI ALT IF NECESSARY NOTE The fire bottle will not discharge with the fuel valve ON F If FIRE warning goes OFF LAND AS SOON AS PRACTICAL F If FIRE warning remains ON LAND IMM...

Page 90: ...ing to a hard surface or other suitable area If possible select an approach direction that offers a left quarter ing headwind to reduce the touchdown ground speed and the amount of right yaw NOTE Touc...

Page 91: ...educe power and altitude with collective if necessary F As the ground is approached rotate both twist grips simultaneously to IDLE and perform a hovering autorotation Avoid rotating twistgrips with co...

Page 92: ...CAL STABILIZER POSITION INDICATOR RIGHT VERTICAL STABILIZER POSITION INDICATOR MID RANGE DEFLECTION POINT L R VERTICAL STAB L R VERTICAL STAB FIN TRAILING EDGE DEFLECTION INDICATORS F92 023 Figure 3 3...

Page 93: ...eric display Conditions Single system failure loss of pressure Procedures F Decrease air speed to below 100 KIAS NOTE A stiffness in the anti torque pedals will occur with a failure of the number 2 sy...

Page 94: ...flight 3 10 PITOT STATIC SYSTEM MALFUNCTION SINGLE OR DUAL PITOT TUBE INSTALLATION STATIC SYSTEM MALFUNCTION Indications Altimeter and IVSI if installed show no change in indication during climb desc...

Page 95: ...LLOW NG HIGH WARNING ANNUNCIATOR RED NG HIGH CAUTION ANNUNCIATOR YELLOW GENERATOR OUT CAUTION ANNUNCIATOR YELLOW GENERATOR HIGH LOAD CAUTION ANNUNCIATOR YELLOW GENERATOR LOAD DIGITAL DISPLAY WHITE F92...

Page 96: ...Y ENGINE HIGH OIL PRESSURE NOTE The red high engine oil pressure annunciator is only activated during the lamp test mode Indications Upper yellow caution annunciator ON if the oil pressure is greater...

Page 97: ...nditions In flight F Land as soon as practical NG HIGH Indications Red warning or yellow caution annunciator ON Procedures F Reduce power to normal range F Check engine torque and EGT indications NG L...

Page 98: ...tions Yellow GEN annunciator ON and LOAD is 0 Procedures F L GEN or R GEN or both if dual generator failure switch RESET F If GEN annunciator still ON OFF FOR AFFECTED GENERATOR S F Continue flight F...

Page 99: ...TOR YELLOW TRANSMISSION HIGH OIL PRESSURE CAUTION ANNUNCIATOR YELLOW TRANSMISSION LOW OIL PRESSURE CAUTION ANNUNCIATOR YELLOW TRANSMISSION LOW OIL PRESSURE WARNING ANNUNCIATOR RED FIRE WARNING ANNUNCI...

Page 100: ...ation without oil for 30 minutes at a power setting of 56 Indications Lower yellow caution annunciator ON Procedures F Land as soon as practical TRANSMISSION OIL PRESSURE HIGH Indications Upper yellow...

Page 101: ...ER IMPENDING BY PASS CAUTION YELLOW FUEL FILTER IMPENDING BY PASS CAUTION FUEL SHUTOFF VALVE YELLOW NOTE 1 FUEL SHUTOFF VALVE YELLOW NOTE 1 C INDICATES LOW FUEL PRESSURE ON BOTH FUEL BOOST PUMPS OR BO...

Page 102: ...el standard day conditions 6000 LBS gross weight Procedures F With low fuel warning tick mark ON 140 KIAS MAXIMUM AND AVOID UNCOORDINATED TURNS MANEUVERS FUEL BOOST PUMP FAILURE Indications Alternatin...

Page 103: ...ng consumption and time calculations DUAL FUEL PROBE FAILURE Indications Digital fuel quantity indicator blanked Vertical quantity segments blanked NOTE The low fuel warning tick mark indication remai...

Page 104: ...N Indications Two yellow bar segments flashing above and below the fuel flow line to the left or right of center Conditions Fuel valve not fully opened closed Procedures F In flight F F Continue fligh...

Page 105: ...CAUTION ANNUNCIATOR YELLOW IIDS MALFUNCTION CAUTION ANNUNCIATOR YELLOW HYDRAULIC SYSTEM PRESSURE OR HIGH TEMPERATURE CAUTION ANNUNCIATOR YELLOW CABIN HEAT WARNING ANNUNCIATOR RED BATTERY WARM CAUTION...

Page 106: ...ircraft F Service or replace battery prior to next flight Overheated battery can cause burns to personnel unless protective clothing and adequate tools are utilized In some instances the battery may c...

Page 107: ...in the battery being disconnected from the aircraft electrical system once a generator is placed on line Generator power alone is not sufficient to start an engine Procedures F Utilize a GPU to start...

Page 108: ...ossible CABIN DOOR Indications Yellow CABIN DOOR annunciator ON Conditions On ground Procedures F Close and safe lock door Conditions In the air Procedures F Reduce airspeed to 60 KIAS Ref Section II...

Page 109: ...HER MALFUNCTION ADVISORIES IIDS FAILURE Indications IIDS displays blanks Conditions Loss of electrical power to IIDS Procedures On ground F Shut down Procedures In flight F Reduce airspeed to 100 KIAS...

Page 110: ...sition Procedures NOTE In the event that the malfunction results in one door remaining closed after the aircraft has gone beyond the threshold airspeed of 47 KIAS the engine with the closed NACA door...

Page 111: ...Each cabin door window may be used as an emergency exit by pulling the emergency exit pull tab and pulling the window inward EMERGENCY EXIT PULL TAB TO REMOVE WINDOW F92 029 EMERGENCY EXIT RELEASE COC...

Page 112: ...ide of the center console It detaches from the mounting bracket by unfastening the quick release clamps The extin guisher uses Halon 1211 extinguishing agent The fire extinguisher is equipped with a p...

Page 113: ...Mounted Typical 4 18 Figure 4 5 Circuit Breakers Baggage Compartment Mounted Typical 4 19 Figure 4 6 Collective Pitch Stick Controls Typical 4 20 Figure 4 7 Cyclic Stick Grip 4 21 4 4 Engine Pre Star...

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Page 115: ...nce of corrosion 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 de...

Page 116: ...CSP 900RFM206E 1 ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E Normal Procedures FAA Approved Original 4 2 F92 031 1A Figure 4 1 Pilot s Preflight Guide Sheet 1 of 2...

Page 117: ...CSP 900RFM206E 1 Normal Procedures ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E FAA Approved Original 4 3 F92 031 2 Figure 4 1 Pilot s Preflight Guide Sheet 2 of 2...

Page 118: ...attery compartment BATTERY CONNECTED SECURE F Battery compartment door CONDITION CLOSED F Pitot tube s CONDITION FREE OF OBSTRUCTIONS F Windscreen CONDITION F Chin windscreen CONDITION F F Chin windsc...

Page 119: ...lanyard to assure tank is full by noting fuel level on the inside of filler neck Ref SECTION VIII Fuel can be trapped in filler neck by the flapper valve F Lighting control panel CHECK OPERATION OF L...

Page 120: ...controls AS DESIRED F F Loose equipment STOWED NOTE Nothing stowed under seats that are to be occupied RIGHT FORWARD TRANSMISSION DECK F Hydraulic System F F Hydraulic manifold CHECK MOUNTING AND FLU...

Page 121: ...CK MOUNTING AND CONDITION F Forward outside engine mount CHECK MOUNTING AND CONDITION F Engine drive shaft CHECK F Fan drive shaft CHECK F Rotor brake CHECK F Transmission deck CHECK FOR FOREIGN OBJEC...

Page 122: ...gine air inlet with particle separator F F Particle separator CHECK NO OBSTRUCTIONS F F Bypass door CLOSED CONDITION OF SEAL F F NACA inlet door CLOSED NO OBSTRUCTIONS F Right Engine F F Engine oil ac...

Page 123: ...feathering bearing CHECK F Pitch change housing CHECK F Blade attach pins CHECK F Blade attach points CHECK F Rotor blades CHECK F Top of rotor head CHECK FUSELAGE RIGHT REAR F Fuselage skin CHECK F E...

Page 124: ...tating cone CHECK FOR FREEDOM OF ROTATION F F Place hands at the 11 and 5 o clock positions and press inward while rotating the cone to the left and right Repeat check by using the 1 and 7 o clock pos...

Page 125: ...and abrasion strips CHECK F F Forward spacer fitting crosstube CHECK F F Skid tube step SECURITY CONDITION F Underside of fuselage F F Fuel catch can drain if installed DRAIN F F Fuselage skin CHECK...

Page 126: ...der seats that are to be occupied F Co pilot pedals if installed ADJUSTED ADJUSTMENT PINS ENGAGED F Crew door CLOSE F Avionics access panel CHECK F Static port CHECK NO OBSTRUCTIONS F Fwd fuel vent fa...

Page 127: ...ss door CHECK OPERATION AND CONDITION CLOSE LEFT CENTER TRANSMISSION DECK F Oil cooler F F Cooling air inlet NO OBSTRUCTIONS F F Oil cooler CHECK MOUNTING AND CONDITION F F Air ducts CHECK MOUNTING AN...

Page 128: ...ICATOR F Transmission access door latches hinges and door CHECK OPERATION CLOSE F Cabin door closed open and latched secured CHECK FUSELAGE LEFT TOP REAR F Engine air inlet w o particle separator F F...

Page 129: ...orm these checks prior subsequent flights of the same day F Fluid levels CHECK F Transmission deck signs of fluid leakage CHECK F Air inlet screens particle separators CHECK F Fuel cap access doors an...

Page 130: ...E Normal Procedures FAA Approved Original 4 16 FE92 032 1 IIDS AIRSPEED INDICATOR MAGNETIC COMPASS ALTIMETER IVSI FOOT HEATER CONTROL VALVE ALTERNATE STATIC SOURCE TOGGLE VALVE VSCS INDICATOR ATTITUDE...

Page 131: ...MANUAL MD900 With PW 206E FAA Approved Original 4 17 FE92 032 2 ALTERNATE STATIC SOURCE TOGGLE VALVE ALTERNATE STATIC SOURCE TOGGLE VALVE FOR LEFT SIDE NOTE 1 NOTE 2 NOTE 1 NOTE 2 PITOT STATIC INSTRU...

Page 132: ...BOTTLE PRI ALT LEFT OFF RIGHT OFF ON OFF FUEL SHUTOFF DISCHARGE O F F ELECTRICAL MASTER AVIONICS L GEN R GEN POWER ON OFF RESET RESET ON ON OFF OFF OFF BAT EXT ESNTL LIGHTING CONTROL LT MSTR CONSOLE...

Page 133: ...PITOT HEAT2 ATT GYRO2 CNDSR FAN 2 IIDS TRAK STB CFU AV FAN IPS ATT GYRO1 LAND LGT CNDSR FAN 1 ADF2 RADAR RT RADAR IND RADAR INVTR RAD ALT MKR BCN COM2 XPNDR 2 DIR GYRO2 NAV 2 L R L R L R L R BST PMP...

Page 134: ...T USED 4 HOVER AND LANDING LIGHT SWITCH 5 SEARCH LIGHT SWITCH SEE NOTE 6 GO AROUND SELECT SWITCH 7 COMMUNICATIONS SELECT SWITCH 8 BLANK 9 VSCS SYNCHRONIZATION SWITCH 10 LEFT RIGHT ENGINE TWIST GRIPS 1...

Page 135: ...1 Normal Procedures ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E FAA Approved Original 4 21 CYCLIC TRIM FLOAT INFLATION SWITCH RADIO ICS F92 036 AUTO PILOT DISENGAGE CARGO HOOK RELEASE Figure 4 7 Cycl...

Page 136: ...K STATIC POSITION SET F Collective Control F F Collective friction ON F F Collective stick position FULL DOWN If collective is not full down do not try to force down until hydraulic pressure increases...

Page 137: ...F F POWER OFF F Fuel system panel F F L BOOST AND R BOOST OFF F F LEFT RIGHT FUEL SHUTOFF ON COVER CLOSED F Engine control panel F F L ENGINE and R ENGINE OFF ELECTRICAL POWER ON F Electrical master...

Page 138: ...or R ENGINE SET TO IDLE FLY AS REQUIRED Monitor EGT NG and starter limits during start If EGT is observed rising above 700 C abort the start as follows Engine control switch OFF monitor IIDS displays...

Page 139: ...GEN ON F F GPU DISCONNECT 4 6 ENGINE RUNUP F Electrical master panel F F Avionics ON AS DESIRED F Engine control panel F F L ENGINE and R ENGINE FLY 4 7 BEFORE TAKEOFF F Cyclic response check F F Move...

Page 140: ...y 10 minutes of flight 4 9 CRUISE If desired press the VSCS Synchronization switch left or right for three seconds to reset the VSCS to the current lateral acceleration and yaw rate 4 10 SLOW FLIGHT A...

Page 141: ...in excess of 9 51 will result in the tail skid contacting the landing surface F927 098 9 51 32 IN 81cm Figure 4 8 Tail Skid to Landing Surface Clearance Running landing Maximum recommended ground cont...

Page 142: ...CTION ON F Cyclic stick TRIM TO NEUTRAL REF FIGURE 4 9 F Pedals NEUTRAL F Engine control panel F F L ENGINE and R ENGINE SET TO IDLE F All unnecessary electrical equipment OFF F Utility panel F F Heat...

Page 143: ...OFF F F Engine control switch for selected engine SET TO IDLE OBSERVE STARTER TIME LIMITS F F Engine control switch for selected engine OFF Normal shutdown continued F Rotor brake F F Raise brake hand...

Page 144: ...ERING STRAP IN STOWED POSITION CENTERING STRAP IN EXTENDED POSITION CENTERING DECAL CENTERING STRAP 90 F92 037 Figure 4 9 Cyclic Centering 4 13 POST FLIGHT F Aircraft investigate any suspected damage...

Page 145: ...oise while flying the helicopter 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 nois...

Page 146: ...Section VI for weight and balance data with doors opened or removed One or both cabin doors may be opened or closed in flight at airspeeds up to 60 KIAS For sustained flight with the cabin doors open...

Page 147: ...ly and excursions into those limits require recording in the engine log book and may increase the maintenance required See Section VIII for recording and maintenance action requirements Pilots should...

Page 148: ......

Page 149: ...om 0 C to 36 C at VY OEI MCP and 4000 LB Gross Weight 5 11 Figure 5 7 Single Engine Rate of Climb and Descent From 10 C to 50 C at VY OEI MCP and 4000 LB Gross Weight 5 12 Figure 5 8 Single Engine Rat...

Page 150: ...limb AEO at VY TOP 4500 Pounds Gross Weight 5 32 Figure 5 27 Rate of Climb AEO at VY TOP 5000 Pounds Gross Weight 5 33 Figure 5 28 Rate of Climb AEO at VY TOP 5500 Pounds Gross Weight 5 34 Figure 5 29...

Page 151: ...10 Height Velocity Diagram 5 49 Figure 5 41 Height Velocity Diagram 5 49 5 11 Power Assurance Check Automatic 5 50 Figure 5 42 Power Assurance Check Menu 5 50 5 12 Power Assurance Check Manual 5 52 F...

Page 152: ......

Page 153: ...nt installed unless otherwise noted 5 2 NOISE CHARACTERISTICS NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be accepta...

Page 154: ...t and note density altitude Pressure altitude is found by setting 29 92 1013 mb in Kolsman window altimeter error To determine true airspeed convert indicated airspeed IAS to calibrated airspeed CAS u...

Page 155: ...40 2000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 DENSITY ALTITUDE FEET 0 98 1 00 1 02 1 04 1 06 1 08 1 10 1 12 1 14 1 16 1 18 1 20 1 22 1 24 1 26 1 28 1 30 1 32 1 34 1 36 TEMPERATURE...

Page 156: ...ition error equals calibrated airspeed CAS Use of chart Use the chart as illustrated by the example To determine calibrated airspeed the pilot must know the indicated airspeed NOTE The example below r...

Page 157: ...Data ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E FAA Approved Original 5 5 160 140 120 100 80 60 40 20 160 140 120 100 80 60 40 20 INDICATED AIRSPEED KNOTS CALIBRATED AIRSPEED KNOTS F92 040 Figure 5...

Page 158: ...t 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 8 000 feet Method Enter the left s...

Page 159: ...IGHT MANUAL MD900 With PW 206E FAA Approved Original 5 7 20 25 30 35 40 45 50 55 60 65 70 75 80 INDICATED AIRSPEED KNOTS 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 F92 041 DENSITY ALTIT...

Page 160: ...These charts based on an electrical load of 30 heater off and air conditioning off Use of Chart The following example explains the correct use of the chart in Figure 5 4 Use of Charts Use the chart a...

Page 161: ...14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 1800 RATE OF CLIMB AT VY FT MIN 10 C 0 C 2...

Page 162: ...12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 1800 RATE OF CLIMB AT VY FT MIN OAT 10 C 0 C 10...

Page 163: ...000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 2A Continuous OEI Po...

Page 164: ...00 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 1A Continuous OEI Power Vy...

Page 165: ...0 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 20 C 30 C 36 C 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 3A Cont...

Page 166: ...00 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 4A 10 C 20 C 40 C 30 C 50...

Page 167: ...00 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 6A Continuous OEI Pow...

Page 168: ...00 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 5A 10 C 20 C 40 C 30 C 50...

Page 169: ...9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 8A Continuous...

Page 170: ...00 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 7A Continuous OEI Power Vy...

Page 171: ...9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 RATE OF CLIMB AT VY FT MIN Continuous OEI Power Vy 5750 lb MA...

Page 172: ...000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 9A 20 C 30 C 36 C 10 C 20...

Page 173: ...000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET 600 400 200 0 200 400 600 800 1000 1200 1400 1600 19000 20000 OAT 10 C 0 C RATE OF CLIMB AT VY FT MIN F92 042 10A 20 C 30 C 36 C 10 C 2...

Page 174: ...best rate of climb speed NOTE These charts based on an electrical load of 30 heater off and air conditioning off Use of Chart The following example explains the correct use of the chart in Figure 5 17...

Page 175: ...18000 17000 16000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 50 C 19000 20000 700 900 1100 1300 1500 1700 1900...

Page 176: ...40 C 30 C 18000 17000 16000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN MAXIMUM OAT LIMIT 50 C 19000 20000 700...

Page 177: ...000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 OAT 10 C 0 C 10 C 20 C 40 C 30 C 50 C 400 600 800 1000 12...

Page 178: ...15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 OAT 10 C 0 C 10 C 20 C 40 C 30 C 50 C 400 600 800 1000...

Page 179: ...000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 OAT C 10 C 0 C 10 C 20 C 40 C 30 C 50 C 400 600 800...

Page 180: ...16000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 OAT 10 C 0 C 10 C 20 C 40 C 30 C 50 C 400 600 80...

Page 181: ...000 16000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 OAT 10 C 0 C 10 C 20 C 40 C 30 C 50 C 400 600...

Page 182: ...00 17000 16000 15000 14000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 50 C 19000 20000 1100 1300 1500 1700 1900 2100 2300...

Page 183: ...10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 30 C 36 C 20 C 1100 1300 1500 1700 1900 2100...

Page 184: ...000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 20 C 1100 1300 1500 1700 1900 2100 2300 2...

Page 185: ...1000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 20 C 1100 1300 1500 1700 1900 2100 2300...

Page 186: ...00 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 20 C OAT 200 400 600 800 1000 1200 1...

Page 187: ...2000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 20 C OAT 200 400 600 800 1000 1200...

Page 188: ...0 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 13000 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN 19000 20000 10 C 0 C 10 C 20 C 40 C 30 C 50 C 20 C OAT 200 400 600 800 1000 1...

Page 189: ...ns a reduction in gross weight capability still allows the aircraft to operate at a maximum gross weight of 6250 LB Follow the example shown below Use of Chart The following example explains the corre...

Page 190: ...16000 8000 5000 OAT C NOTE GROSS WEIGHTS ABOVE 6250 LB PROVIDED FOR CALCULATION PURPOSES ONLY DO NOT EXCEED 6250 LB GROSS WEIGHT LIMIT 4000 3000 2000 1000 PRESSURE ALTITUDE FEET THIS CHART BASED ON W...

Page 191: ...CABIN HEAT ON 40 30 20 10 0 10 20 30 40 50 60 OAT C NOTE GROSS WEIGHTS ABOVE 6250 LB PROVIDED FOR CALCULATION PURPOSES ONLY DO NOT EXCEED 6250 LB GROSS WEIGHT LIMIT PRESSURE ALTITUDE FEET THIS CHART...

Page 192: ...EIGHT 6250 LB WEIGHTS IN EXCESS OF 6250 LB MUST BE EXTERNAL AND JETTISONABLE GROSS WEIGHT LB 11000 10000 9000 7000 6000 13000 14000 15000 12000 16000 8000 5000 4000 3000 2000 1000 0 PRESSURE ALTITUDE...

Page 193: ...C ON GROSS WEIGHT LB OAT C NOTE MAXIMUM INTERNAL GROSS WEIGHT 6250 LB WEIGHTS IN EXCESS OF 6250 LB MUST BE EXTERNAL AND JETTISONABLE 4900 5000 5100 5200 5300 5400 5500 5600 5700 5800 5900 6000 6100 6...

Page 194: ...000 12000 16000 8000 5000 OAT C NOTE GROSS WEIGHTS ABOVE 6250 LB PROVIDED FOR CALCULATION PURPOSES ONLY DO NOT EXCEED 6250 LB GROSS WEIGHT LIMIT 4000 3000 2000 1000 PRESSURE ALTITUDE FEET THIS CHART B...

Page 195: ...R CABIN HEAT ON 40 30 20 10 0 10 20 30 40 50 60 OAT C NOTE GROSS WEIGHTS ABOVE 6250 LB PROVIDED FOR CALCULATION PURPOSES ONLY DO NOT EXCEED 6250 LB GROSS WEIGHT LIMIT THIS CHART BASED ON WINDS 3KTS OR...

Page 196: ...0 14000 15000 12000 16000 8000 5000 OAT C 4000 3000 2000 1000 PRESSURE ALTITUDE FEET 0 GROSS WEIGHT LB THIS CHART BASED ON WINDS 3KTS OR LESS AND 15 ELECTRICAL LOAD FOR ELECTRICAL LOADS ABOVE BELOW 15...

Page 197: ...ERNAL AND JETTISONABLE 4900 5000 5100 5200 5300 5400 5500 5600 5700 5800 5900 6000 6100 6200 6300 6400 4800 4700 4600 GROSS WEIGHT LB 4500 6500 6600 6700 6800 6900 MAXIMUM TEMPERATURE FOR CABIN HEAT O...

Page 198: ...weight for hover OGE at 2 5 minute OEI power Known HP 4000 FT OAT 10 C Method Enter the chart at 10 C and move right to the 4000 HP curve At this point move up and read from the gross weight scale 49...

Page 199: ...CABIN HEAT OFF HEADWIND KNOTS GROSS WEIGHT 3500 3700 3900 4100 4300 4500 4700 4900 5100 5300 5500 5700 5900 6100 6300 6500 POUNDS 0 5 10 15 20 25 30 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5...

Page 200: ...5200 5300 5400 5500 GROSS WEIGHT POUNDS 3900 3800 3700 3600 3500 50 40 30 20 10 0 10 20 30 40 50 60 OAT C PRESSURE ALTITUDE FEET 11000 10000 9000 8000 6000 5000 4000 3000 1000 0 12000 13000 2000 POUN...

Page 201: ...ON OF CHART B THE AVOID AREA IN CHART A APPLIES CHART B F92 046A Figure 5 41 Height Velocity Diagram The clear area of Figure 5 41 Chart B represents density altitude gross weight combinations for whi...

Page 202: ...menu or other previous power assurance checks in the TREND LOG under AIRD CRAFT MONITOR menu NOTE This power check procedure refers to the automated IIDS power check If unable to perform the automated...

Page 203: ...engine is to be checked first press the to access the right engine menu RT ENG TQ XXX X TIME 30 SEC F Stabilize engine torque at 3 of the ENG TQ value displayed for 30 seconds The IIDS provides a cou...

Page 204: ...e the Engine Torque Chart Ref Figure 5 43 to determine the torque value to be utilized based on the OAT and pressure altitude recorded in the previous step F Increase collective and stabilize at the p...

Page 205: ...bove noted conditions is determined to be Engine torque 71 Utilizing the EGT and NG Power Check Charts Ref Figure 5 44 and Figure 5 45 the maximum values for EGT and NG for the above noted conditions...

Page 206: ...6E Performance Data FAA Approved Original 5 54 F92 048 20 10 0 10 20 30 40 35 40 45 50 55 60 65 70 75 80 ENGINE TORQUE PRESSURE ALTITUDE FEET AMBIENT TEMPERATURE C 50 12000 6000 8000 14000 16000 10000...

Page 207: ...a ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E FAA Approved Original 5 55 F92 049 900 850 800 750 700 650 600 550 AMBIENT TEMPERATURE C 40 20 0 20 40 60 PRESSURE ALTITUDE FEET 4000 8000 SEA LEVEL 500 1...

Page 208: ...rmance Data FAA Approved Original 5 56 F92 050 1 NG 36 40 30 20 10 0 10 20 30 40 50 AMBIENT TEMPERATURE C 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 PRESSURE ALTITUDE FEET 8000 16000 12000 4000 SEA...

Page 209: ...E FAA Approved Original 5 57 5 58 blank F92 050 2 40 30 20 10 0 10 20 30 40 50 60 AMBIENT TEMPERATURE C 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 NG PRESSURE ALTITUDE FEET 16000 12000 8000 4000 200...

Page 210: ......

Page 211: ...6 4 Longitudinal Weight and Balance Determination Passenger Configuration 6 8 EXAMPLE I Longitudinal CG Determination Passenger 6 8 6 5 Longitudinal Loading of Cargo 6 9 EXAMPLE II Longitudinal CG Det...

Page 212: ...lance Data CSP 900RFM206E 1 ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E Original 6 ii PARAGRAPH PAGE Table 6 9 Weight and Lateral Moments Pilot and Passengers 6 21 Table 6 10 Weight and Lateral Moment...

Page 213: ...is located at Station 199 3 Cargo Deck Capacity 1500 pounds not to exceed 115 pounds per square foot Baggage compartment limit sta 234 3 to 256 9 500 pounds not to exceed 115 lbs per square foot Ulti...

Page 214: ...202 204 206 6500 6000 5500 5000 4500 4000 3500 3000 FUSELAGE STATION IN WEIGHT POUNDS F92 051 208 NORMAL CG LIMITS 6500 6000 5500 5000 4500 4000 3500 3000 LATERAL CG STATION IN WEIGHT POUNDS 5 4 3 2...

Page 215: ...nd Balance Data Original 6 3 15 85 15 85 STA 130 7 STA 173 0 0 0 19 0 19 0 STA 213 0 STA 245 6 CG OF PILOT OR COPILOT PASSENGER CG REAR FACING PASSENGERS CG FWD FACING PASSENGERS CL OF BAGGAGE COMPART...

Page 216: ...230 5 FRAME 3 16 220 200 180 160 140 120 100 80 60 STA 292 817 WL 147 WL 159 ROOF DECK 60 80 100 120 140 180 200 220 240 260 280 300 320 340 360 380 400 420 440 460 STA 199 25 WL 207 97 160 5 0 F92 05...

Page 217: ...ISTRATION NUMBER N9XXXX PAGE 4 OF 4 DESCRIPTION OF ARTICLE WEIGHT CHANGE RUNNING TOTAL BASIC AIRCRAFT ADDED REMOVED WEIGHT LONG ARM WEIGHT LONG ARM Form HOQ014 rev 5 00 12 23 xx 01 09 xx 01 09 xx X AC...

Page 218: ...233 0 BL 23 3 FWD JACK POINT STA 154 1 BL 0 0 NOTE IN A LEVEL ATTITUDE MAIN ROTOR MAST IS TILTED 3 DEG FORWARD WEIGHING POINT AVE SCALE READING LBS TARE OR CALIB CORR LBS NET WEIGHT LBS LONGITUDINAL...

Page 219: ...he weight and balance effects of these changes in the Basic Weight and Balance Record inserted in this section Use the balance and station diagrams shown as an aid for weight and balance changes Use t...

Page 220: ...loadings are not symmetrical about the aircraft centerline determine lateral CG s as described in Paragraphs 6 6 and 6 7 EXAMPLE I Longitudinal CG Determination Passenger ITEM WEIGHT LB STATION ARM MO...

Page 221: ...e cargo moment Cargo Moment Cargo Weight X Cargo CG Perform weight and balance as previously described for passenger configura tion EXAMPLE II Longitudinal CG Determination Cargo ITEM WEIGHT LB STATIO...

Page 222: ...in the basic weight and longitudinal moment from The Basic Weight and Bal ance Record Ref Figure 6 4 For pilot and passenger longitudinal and lateral center of gravity stations see Figure 6 2 EXAMPLE...

Page 223: ...orrectnumber of tiedowns in accor dance with Table 6 4 Locate restraint loops in accordance with Figure 6 6 NOTE Cargo carried in the baggage compartment shall not be higher than 36 inches To assure t...

Page 224: ...EXAMPLE IV Tiedown 500 pounds of cargo in the main cabin LATERAL TIEDOWN No FORWARD LEFT RIGHT 1 220 14 220 2 20 40 13 20 40 4 130 40 11 130 40 5 120 220 10 120 220 ____ ____ ____ TOTAL 540 520 520 Si...

Page 225: ...L LEFT LATERAL RIGHT 1 156 8 27 0 220 2 174 9 25 0 20 40 3 193 0 25 0 130 20 4 211 1 25 0 130 40 5 229 2 27 0 120 220 6 229 2 11 0 50 240 7 229 2 8 0 50 240 8 229 2 8 0 50 240 9 229 2 11 0 50 240 10 2...

Page 226: ...ginal 6 14 CARGO RESTRAINT LOCATION 1 2 3 4 5 6 7 8 9 10 12 13 14 15 16 17 18 19 20 21 23 24 25 26 27 28 FWD LEFT RIGHT 11 F92 056 TIEDOWNS 25 AND 26 ARE D RINGS LOCATED AT WL 154 5 TIEDOWNS 19 THRU 2...

Page 227: ...525 550 575 600 625 650 675 700 725 750 775 800 825 850 875 900 925 950 975 1000 FUEL WEIGHT POUNDS F92 057 1 NOTES WEIGHTS AND MOMENTS BASED ON JET A FUEL 2 TOTAL WEIGHT OF FUEL IS DEPENDENT UPON THE...

Page 228: ...0 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775 800 825 850 875 900 925 950 975 1000 NOTES WEIGHTS AND MOMENTS BASED ON JET B FUEL 2 TOTAL WEIGHT OF FUEL IS DEPENDENT UPO...

Page 229: ...0 188 7 96237 80 544 188 9 102787 85 578 189 2 109343 90 612 189 4 115905 95 646 189 6 122470 100 680 189 8 129038 105 714 189 9 135607 110 748 190 1 142176 115 782 190 2 148744 120 816 190 3 155309 1...

Page 230: ...88 188 7 91992 80 520 188 9 98252 85 553 189 2 104519 90 585 189 4 110791 95 618 189 6 117067 100 650 189 8 123345 105 683 189 9 129624 110 715 190 1 135903 115 748 190 2 142181 120 780 190 3 148457 1...

Page 231: ...IN LB MOMENT IN LB 100 13070 17300 21300 120 15684 20760 25560 140 18298 24220 29820 160 20912 27680 34080 180 23526 31140 38340 200 26140 34600 42600 220 28754 38060 46860 240 31368 41520 51120 BAGG...

Page 232: ...800 32400 36000 39600 43200 200 32000 36000 40000 44000 48000 220 35200 39600 44000 48400 52800 240 38400 43200 48000 52800 57600 260 41600 46800 52000 57200 62400 280 44800 50400 56000 61600 67200 30...

Page 233: ...ENT IN LB MOMENT IN LB MOMENT IN LB 100 1585 1900 1900 110 1744 2090 2090 120 1902 2280 2280 130 2061 2470 2470 140 2219 2660 2660 150 2378 2850 2850 160 2536 3040 3040 170 2695 3230 3230 180 2853 342...

Page 234: ...0 1800 100 500 1000 1500 2000 110 550 1100 1650 2200 120 600 1200 1800 2400 130 650 1300 1950 2600 140 700 1400 2100 2800 150 750 1500 2250 3000 160 800 1600 2400 3200 170 850 1700 2550 3400 180 900 1...

Page 235: ...13 Figure 7 7 Upper Flight Controls Subsystem 7 14 Figure 7 8 Anti Torque Controls Subsystem Sheet 1 of 3 7 16 Figure 7 8 Anti Torque Controls Subsystem Sheet 2 of 3 7 17 Figure 7 8 Anti Torque Contro...

Page 236: ...orage 7 46 7 16 Balance Monitoring System 7 49 Figure 7 25 Balance Monitoring System Installation 7 49 7 17 IIDS Menu Structures 7 50 Figure 7 26 IIDS Top Level Menus 7 50 Figure 7 27 Time Summary 7 5...

Page 237: ...1 ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E Original 7 iii 7 iv blank PARAGRAPH PAGE Figure 7 43 Aircraft Monitor IIDS Setup 7 67 Figure 7 44 Fuel Calibration 7 68 Figure 7 45 Set Engine Parameters...

Page 238: ......

Page 239: ...computerized track and balance The patented NOTAR anti torque system provides many benefits It results in low noise by locating the fan in the fuselage and eliminating the conventional noisy tail roto...

Page 240: ...AND ENGINE LEFT HAND EMPENNAGE ASSEMBLY UPPER COWLING AND FAIRINGS TRANSMISSION ASSEMBLY TAILBOOM ASSEMBLY ANTI TORQUE THRUSTER BAGGAGE COMPARTMENT DOOR ANTI TORQUE ASSEMBLY CABIN DOOR LANDING GEAR AS...

Page 241: ...are positioned high on the sides of the fuselage in line with the forward edge of the cabin doors and one on the fuselage centerline just above the baggage compartment door Fabric socks are used to ca...

Page 242: ...Exterior The rotor transmission mount consists of an eight legged metal truss that sup ports the mast base and the static mast The transmission gearbox mounts beneath the mast base and the rotor turns...

Page 243: ...oduced by airflow out of the controllable direct jet thruster at the end of the tailboom The empennage consists of the horizontal stabilizer with upper and lower moveable vertical stabilizers located...

Page 244: ...es Provide energy absorbing capabilities during nor mal or severe landings Forward and Aft Saddle Assemblies Provide a means to attach the crosstube assemblies to the fuselage attachment points Side S...

Page 245: ...H SECOND NOTCH GREEN RED EMPTY FULL F92 060 RESERVOIR INDICATOR CLOCKING TYPICAL SKID TUBE FORWARD SPACER FITTING AFT SADDLE ASSEMBLY AFT CROSSTUBE SIDE STOP CLAMP ASSEMBLY PLUG DAMPER ASSEMBLY AFT AB...

Page 246: ...ts The pitchcase is a hollow elliptically shaped graphite epoxy tube that surrounds the flexbeam and is attached to both the flexbeam and the blade at its outboard end by a pair of expandable bushing...

Page 247: ...The plates are grooved to accept the flexbeams and are bolted together with the same bolts that attach the flexbeams The hub mounts to the static mast by a pair of grease lubricated tapered roller bea...

Page 248: ...to the surface of the pitchcase dual jumpers across all joints and twin carbon brushes for hub to mast continuity 7 6 FLIGHT CONTROLS The flight controls provide a means of controlling blade pitch of...

Page 249: ...thrust As the collective stick assembly is moved control linkages increase or de crease the rotor blades angle of attack The collective pitch system includes two automatic control features Convention...

Page 250: ...IENT SPRING ASSEMBLY LONGITUDINAL CONTROLS CONTROL ROD ASSEMBLY LATERAL TRIM ACTUATOR LATERAL CONTROLS BRACKET ASSEMBLY LONGITUDINAL TRIM ACTUATOR CRANK ASSEMBLY LONGITUDINAL GRADIENT SPRING ASSEMBLY...

Page 251: ...ACKET ASSEMBLY COLLECTIVE CONTROL ROD ASSEMBLY COLLECTIVE BELLCRANK ASSEMBLY LONGITUDINAL COLLECTIVE FOD COVER UPPER DECK COLLECTIVE CONTROL ROD ASSEMBLY COLLECTIVE HYDRAULIC SERVOACTUATOR COLLECTIVE...

Page 252: ...in the forward right hand cockpit cabin bulkhead and in the cabin ceiling to transmit the control motions to the dual tandem hy draulic actuators that operate the rotor control mixer and the swashplat...

Page 253: ...as the thruster nozzle opens and closes The hydraulic actuator operates the NOTAR fan blade pitch through a pushrod bellcrank cam linkage and the thruster rotation through a push pull type cable along...

Page 254: ...RECTIONAL PEDAL ASSEMBLY RIGHT HEEL REST SUPPORT LEFT HEEL REST SUPPORT HEEL REST ASSEMBLY DIRECTIONAL CONTROL ROD ASSEMBLY LOWER CLOSET DIRECTIONAL BELLCRANK ASSEMBLY AFT DIRECTIONAL CONTROL ROD ASSE...

Page 255: ...LIMITING CONTROL ROD ASSEMBLY DIRECTIONAL CONTROL CABLE ASSEMBLY DIRECTIONAL CONTROLS CONTROL ROD ASSEMBLY DIRECTIONAL CONTROL ROD ASSEMBLY NOTAR FAN INPUT FORCE LIMITING CONTROL ROD ASSEMBLY SPLITTER...

Page 256: ...STATIONARY CONE ASSEMBLY THRUSTER CONTROL DRUM ASSEMBLY THRUSTER DRUM BRACKET ASSEMBLY THRUSTER CONTROL SECTOR ASSEMBLY THRUSTER CONTROL ROD ASSEMBLY THRUSTER BUILDUP ASSEMBLY ROTATING CONE ASSEMBLY T...

Page 257: ...ilizers Instrumentation control includes a dual indica tor on the instrument panel to show incidence angle of the two vertical stabilizers a LEFT STAB FAIL RIGHT STAB FAIL or TOTAL STAB FAIL yellow CA...

Page 258: ...cyclic pitch function and one for collective pitch of the main rotor The 1 system operates only the main rotor controls while the 2 system operates the main rotor controls and also the NOTAR anti torq...

Page 259: ...21 PRESSURE TRANSDUCER SYSTEM SELECT SOLENOID FLUID LEVEL SIGHT GAUGE FILTER BOWL PRESSURE FILTER BOWL RETURN SYSTEM NO 2 PUMP SYSTEM NO 1 PUMP GSE PANELS BLEED VALVE SAMPLING VALVE TEMPERATURE SWITCH...

Page 260: ...GSE PANEL F92 065 HAND PUMP OPTIONAL MANIFOLD RESERVOIR VARIABLE DELIVERY PUMP VARIABLE DELIVERY PUMP MANIFOLD RESERVOIR COLLECTIVE SERVO ACTUATOR LONGITUDINAL SERVO ACTUATOR LATERAL SERVO ACTUATOR DI...

Page 261: ...es a master cylinder operated by the brake handle in the cockpit and the actuator that operates the disc brake on the back side of the transmission where the NOTAR drive shaft connects A yellow BRAKE...

Page 262: ...14 Each engine is mounted to the fuselage upper deck by a three point adjustable titanium mount The air inlet which is in the middle of the engine is located inside a titanium walled inlet plenum that...

Page 263: ...CHIP DETECTOR OIL FILTER IMPENDING BYPASS INDICATOR OIL FILTER COVER FMU FUEL PUMP FUEL FILTER FUEL NOZZLE FUEL MANIFOLD FMU SHROUD T1 T6 TERMINAL BOX NG SENSOR OIL PRESSURE PORT OIL TEMPERATURE PORT...

Page 264: ...cts the planet gear carrier in the top of the transmission to the main rotor hub through a splined connection at each end The engines and transmission are electrically bonded to the airframe by suitab...

Page 265: ...SHAFT PRESSURE SWITCH LOW MAGNETIC CHIP DETECTOR F92 069 2 Figure 7 15 Drive System Sheet 2 of 2 Engine and transmission lubricating oil is cooled by air oil heat exchangers mounted in the sides of th...

Page 266: ...l guides create a vortex that separates heavy particles from the air The particles drop to the bottom of the particle separator panel A solenoid valve and bleed air lines route engine compressor bleed...

Page 267: ...gine control panel for the left and right engines These switches are gated between OFF and IDLE the switch knobs must be lifted to pass the gates The other switch positions are FLY and TRAIN and are n...

Page 268: ...the appropriate twist grip on the collective stick to modulate the power 7 11 FUEL SYSTEM The single crash resistant elastomeric fuel cell is capable of holding 161 3 U S gallons of jet fuel and is lo...

Page 269: ...SEGMENTS GREEN FUEL LOW WARNING SEGMENT RED LB FUEL FLOW LINE LOW FUEL PRESSURE ANNUNCIATORS YELLOW FUEL FILTER IMPENDING BYPASS ANNUNCIATOR YELLOW FUEL SHUTOFF VALVE POSITION ANNUNCIATOR YELLOW LOW F...

Page 270: ...discreets being open circuit The fuel filter impending bypass status is shown by an inverted U above each fuel line indication VIEW LOOKING AFT VENT ROLLOVER VALVE 4 FWD LH VENT SYS LH FUEL FEED VAPO...

Page 271: ...HT GCU RIGHT AVIONICS RELAY SHUNT 2 LEFT GCU SHUNT 1 ESS PWR ESS PWR BATTERY RELAY RT ESS BUS RELAY RIGHT ESS BUS LEFT ESS BUS BATTERY BUS EXTERNAL POWER RELAY RIGHT DC BUS LEFT DC BUS RT LT LT ESS BU...

Page 272: ...ELECTRICAL LOAD CENTER GENERATOR CONTROL UNIT GENERATOR CONTROL UNIT F92 074 Figure 7 20 Battery Power External Power and DC Power Component Locator The key switch is located on the right hand side o...

Page 273: ...n Threshold Lights 2 Baggage Compartment Floodlight 1 Aircraft Exterior Lighting Nose Fixed Landing Light 1 Fixed Hover Light 1 Empennage Left End of Horizontal Stabilizer Red Navigation Light 1 Right...

Page 274: ...on off valve located on the Utility panel to a pair of ejectors that mix bleed air and ambient air to a desired temperature and flow rate One ejector serves the cockpit the other serves the cabin The...

Page 275: ...GER COMPARTMENT PASSENGER COMPARTMENT EJECTORS ENGINE ENGINE CHECK VALVES START UP LOCK OUT HEAT ON OFF SWITCH DEFOGGING MANIFOLDS FOOT HEATERS FOOT HEATERS CONTROL VALVES FLOW CONTROL VALVES FLOW CON...

Page 276: ...puter Also limit checking on certain parameters is performed to provide the caution warning an nunciation The display is a color Liquid Crystal Display LCD panel which allows the flexibility of integr...

Page 277: ...tion where the pilot observed a problem with the IIDS but didn t notice any failure annunciation Third ease of IIDS maintenance on and off the aircraft These fault words are stored in the Fault Log wh...

Page 278: ...active When the probe voltage goes back above 18 volts for more than one second the vertical scales shall be illuminated A failure of one of thefuel probes causes only the digit values to blank where...

Page 279: ...therefore the displayed torque limits are lower than those for the engine as stated in the Pratt Whitney Maintenance Manual EGT is indicated by two vertical bargraphs and a three digit indicator showi...

Page 280: ...Generator load display LOAD Warning Annunciators displayed in red are shown for engine fire engine oil temperature high engine oil pressure high or low NG high or low transmission area fire transmissi...

Page 281: ...e is cleared Pilots should wait two seconds before selecting a menu option At start up and if required during flight messages are displayed on the alphanumeric display automatically A list of these me...

Page 282: ...check failed W YES Advise Maintenance OVR TORQ LFT 2 30 OVR TORQ RT 2 30 OVR EGT LFT 2 30 OVR EGT RT 2 30 OVR NG LFT 2 30 OVR NG RT 2 30 MTO or OEI over count W NO Advise Maintenance PRES 1 0 PSI PRES...

Page 283: ...f data logs to ground based com puters A YES N A CHECK FAULT LOG Fault Log during flight2 3 A YES Advise Maintenance CHK EXCEED LOG Exceedance Log dur ing flight3 A YES Advise Maintenance CHECK ROTOR...

Page 284: ...uffer loop and will be contin uously over written unless an exceedance occurs or the crew requests a record of an event Exceedances generate both data logs and excee dance logs The data log record pro...

Page 285: ...operating soft ware etc On power up the IIDS uses information in the setup log to compare the current Torque and EGT trim values from the EEC to the values stored in the IIDS setup log to assure the d...

Page 286: ...rew requested Data Log and to enter into memory data that is used to initialize the TIME DATE ENGINE PARM and Cargo Hook CALIB CODE and FUEL CALIBRATION func tions in the IIDS When the key is pressed...

Page 287: ...re 7 28 thru Figure 7 40 The normal sequence of events is for the pilot to request the BMS program from the IIDS by pressing the MENU key on the IIDS panel and paging down the menu to BMS The BMS syst...

Page 288: ...sition Continuous display of altitude ENT Key resets starts and stops timer alternate action CLR Key exits function and resets timer For expanded menu structure Ref Figure 7 28 thru Figure 7 40 For ex...

Page 289: ...ST FLT TIME ENT NOTE 1 THIRD LEVEL MENU FOR RIGHT ENGINE SAME AS FOR LEFT ENGINE POWER MODULE TSO CMPSR TURB CYCLE CNT ACCUM POWER TURB CYCLE CNT ACCUM NOTE TO RETURN TO PREVIOUS HIGHER LEVEL PRESS ME...

Page 290: ...KIAS LAT NOTE 2 120 KIAS LAT X XX IPS AT YY YY NOTE 3 NOTE 2 120 KIAS VERT X XX IPS AT YY YY NOTE 4 NOTE 2 AUTOMATICALLY STEPS THROUGH ACQUIRING MEASUREMENTS SPECIFIED FOR THIS REGIME NOTE 3 WHEN COMP...

Page 291: ...K BMS FAULT LOG BMS VERSION LOG RUN XX M R MEASUREMENTS MAIN ROTOR CONFIGURATION MAIN ROTOR SOLUTION OPTIONS DISPLAY M R SOLUTION RUN XX HOVER IGE LAT X XX IPS AT YY YY 80 KIAS LAT X XX IPS AT YY YY 8...

Page 292: ...ESS MENU NOTAR BALANCE SPECTRUM MAIN ROTOR TRACK RUN XX M R MEASUREMENTS MAIN ROTOR CONFIGURATION MAIN ROTOR SOLUTION OPTIONS DISPLAY M R SOLUTION RUN XX BLADE 1 HUB WT XXX GRAMS BLADE 5 HUB WT XXX GR...

Page 293: ...N XX ADJUSTMENTS USED PCL TAB WEIGHT COMPUTE ENTIRE SOLTN NOTE 1 NOTE 2 NOTE 1 NOTE 2 OPERATOR OPTIONAL SELECTION OR OR OR OR NOTE 2 NOTE 2 NOTE 2 PCL TAB PCL WEIGHT COMPUTE GND SOLTN ONLY COMPUTE 80...

Page 294: ...TO PREVIOUS HIGHER LEVEL PRESS MENU NOTAR BALANCE SPECTRUM MAIN ROTOR TRACK RUN XX M R MEASUREMENTS MAIN ROTOR CONFIGURATION MAIN ROTOR SOLUTION OPTIONS TOP LEVEL SECOND LEVEL THIRD LEVEL FOURTH LEVEL...

Page 295: ...H STROBE BLD SPREAD ON MAIN ROTOR BALANCE NOTE TO RETURN TO PREVIOUS HIGHER LEVEL PRESS MENU NOTAR BALANCE SPECTRUM MAIN ROTOR TRACK DEFAULT OR FLASH STROBE BLD SPREAD OFF TOP LEVEL SECOND LEVEL THIRD...

Page 296: ...R WEIGHT CONFIGURATION DISPLAY NOTAR SOLUTION RUN XX FLY 100 GND PRESS REC ACQUIRING 100 GND RADIAL 100 GND RADIAL X XX IPS AT YY YY ACQUISITION COMPLETE NOTE 2 WHEN COMPLETE RESULT DISPLAYED FOR 4 SE...

Page 297: ...T ACQUIRED OR OR NOTAR SOLUTION NOT MADE TOP LEVEL SECOND LEVEL THIRD LEVEL FOURTH LEVEL COMPUTING NOTAR SOLTN RUN XX XX SUB XXX GRAMS STD XX NOT MADE NOTE 1 ENT KEY SELECTS DIGITS TO BE EDITED AND KE...

Page 298: ...OTE 1 GATHERING TREND SET XX SPC XX XX NOTE 1 TREND SPECTRUM SET XX COMPLETE NOTE 2 NOTE 1 NOTE 2 NOTE 1 NOTE 2 NOTE 1 AUTOMATICALLY STEPS THROUGH ACQUIRING MEASUREMENTS SPECIFIED FOR THIS REGIME NOTE...

Page 299: ...VEL PRESS MENU NOTAR BALANCE SPECTRUM MAIN ROTOR TRACK BMS OK DBASE USAGE XXX ADVISORIES XX END OF BMS FAULT LOG OR BMS ADVISORY LOG BMS FAULT LOG BMS VERSION LOG BMS MAINTENANCE BALANCE OK END OF BMS...

Page 300: ...XX XX BMSBP CHECKSUM XXXXXXXX NOTAR BALANCE SPECTRUM MAIN ROTOR TRACK MAIN ROTOR MODEL VER XX XXX BMSOP VER XX XXX P N XXXXX XX BMSOP CHECKSUM XXXXXXXX NOTAR MODEL VER XX XXX VIB MONITOR VER XX XXX SP...

Page 301: ...G BMS VERSION LOG BMS MAINTENANCE TOP LEVEL SECOND LEVEL THIRD LEVEL NOTE 1 FOR ALL CLEAR MENU SELECTIONS PRESS ENT KEY AND A PRESS TO CLEAR MESSAGE WILL BE DISPLAYED PRESS REC KEY TO CLEAR THE LOG AN...

Page 302: ...SEC TO T2 XX SEC ABV T2 XX SEC TO T3 XX SEC ABVT3 XX SEC TO T4 XX SEC ABV T4 XX NOTE PRESSING THE BUTTON WILL TAKE YOU TO THE PREVIOUS HIGHEST MENU LEVEL MENU F92 096 TOP LEVEL SECOND LEVEL THIRD LEVE...

Page 303: ...XX LEFT ENGINE DATE TIME NP XXX T1 XC TORQUE XX NG XX EGT XXXC P0 XXXX FT OAT XX C PERFORM MARGIN L PA CK NG XX L PA CK EGT XX NG COR FTR XX X EGT COR FTR XXX NOTE PRESSING THE BUTTON WILL TAKE YOU TO...

Page 304: ...0 RIGHT EEC DSCWD1 RIGHT EEC MENU SAME AS LEFT EEC MENU NOTE PRESSING THE BUTTON WILL TAKE YOU TO THE PREVIOUS HIGHEST MENU LEVEL MENU TOP LEVEL SECOND LEVEL THIRD LEVEL F92 098 EXCEEDANCE LOG TREND L...

Page 305: ...G INSTAL ROTOR BRK INSTAL FAULT LOG IIDS SETUP TREND LOG FWD FUEL CAL XXX AFT FUEL CAL XXX TOP LVL SFTWR PN XXXXXXXXXXXX A C NO XXXXXXXX CFG DAT MM DD YY CFG TIM HR MN SE OPER SFTWR PN XXXXXXXXXXXX MA...

Page 306: ...LEVEL MENU APPEARS NOTE 2 ENT SELECTS DIGITS TO BE EDITED AND KEYS CHANGE SELECTED DIGITS REC KEY STORES SELECTION CLR EXITS TO BLANK DISPLAY NOTE 3 PRESS ENT FOR MORE THAN 4 SECONDS COMMANDS CALIBRAT...

Page 307: ...ED AND KEYS CHANGE SELECTED DIGITS REC KEY STORES SELECTION CLR EXITS TO BLANK DISPLAY F92 101 TOP LEVEL SECOND LEVEL Figure 7 45 Set Engine Parameters SET TIME DATE NOTE TO RETURN TO PREVIOUS HIGHER...

Page 308: ......

Page 309: ...e Access Panels 8 12 Figure 8 6 Left Side Access Panels 8 13 Figure 8 7 Right Side Access Panels 8 14 Figure 8 8 Top View Access Panel 8 15 Figure 8 9 Bottom View Access Panels 8 16 Figure 8 10 Stabil...

Page 310: ...gine Charts 8 38 Figure 8 23 EGT Vs Time All Conditions Except Starting 8 38 Figure 8 24 EGT Vs Time Starting 8 39 Figure 8 25 Power Turbine NP Speed Vs Time 8 39 Figure 8 26 Compressor Turbine NG Spe...

Page 311: ...plorer by hand and for towing The wheels are manually lowered with a detachable jack handle and are held in the down position by a mechanical lock The ground handling wheel set is equipped with a tow...

Page 312: ...tion for a non operating rotor is not to exceed four feet up maximum Measurement to be taken from static rest Helicopter Towing The towbar is equipped with caster wheels and is designed for use with t...

Page 313: ...hand brake to the rear tires and has a 10 000 lb 4540 Kg capacity Ensure all stress panels listed in Figure 8 1 1 are installed Airframe structure damage can occur if stress panels are not in place b...

Page 314: ...d by the prevailing weather conditions length of storage parking and location Forward and aft tiedowns Each tiedown Ref Figure 8 2 has a quick connect fitting with a streamer attached REMOVE BEFORE FL...

Page 315: ...ster Tighten cover with strap assembly Pitot tube cover The pitot cover Ref Figure 8 2 is vinyl and reinforced with galvanized steel staples at stress points A bright red warning streamer REMOVE BEFOR...

Page 316: ...ginal 8 6 UPPER DECK COVER F92 104A BUBBLE COVER BLADE COVER BOOM COVER ENGINE AREA COVER THRUSTER COVER ROTOR HUB COVER AFT UPPER TIEDOWN FORWARD UPPER TIEDOWN BLADE TIEDOWN PITOT TUBE COVER AFT LOWE...

Page 317: ...ows attachment of tiedown ropes Blade covers cold weather The MD Explorer cold weather blade covers are similar to the standard blade covers but are fitted with full length zippers and heater hose boo...

Page 318: ...of debris and kept open during storage period Store helicopter in hangar if space allows Statically ground helicopter Ref Figure 8 3 Flyable Storage Flyable storage will maintain a stored MD Explorer...

Page 319: ...Figure 8 2 If a paved ramp with tiedown rings are not available park helicopter on an unpaved parking area headed in the direction from which highest forecast winds are expected Install blade tiedown...

Page 320: ...em access method and fastener type Reference Designator The number indicates the nearest attaching fuselage station The letter indicates the location N Nose L Left Side R Right Side T Top Side B Botto...

Page 321: ...LOCK COUNTERCLOCKWISE LOCK CLOCKWISE UNLOCKED 1 4 TURN SCREW BOLT PULL TO RELEASE DOOR PINS SLEEVE BOLT LEVER ACTION HANDLE CAMLOC 2 PULL 1 PUSH KEYLOC CAMLOC LATCH LOCKED HINGE LOCKED UNLOCKED PUSH T...

Page 322: ...N82 N106 Removal and Installation Item No Name Permits Access To Quantity Type Method Ref Figure 8 4 N80 Nose Door Pitot Static System Battery 2 1 Latch Keyloc B A N82 Panel Landing Light Flight Contr...

Page 323: ...rgo Compartment 1 Lever Action Handle H L210 Xmsn Access Door As sembly LH Main Transmission Access Engine Reduction Gearbox Housing 3 5 2 Latch or Camloc Hinge C E or U D L210 Transmission Access Doo...

Page 324: ...ch or Camloc Hinge C E or U D R158 Fuel Cap and Adapter Fuel Filler Neck 1 Turn and Lock S R166 Passenger Door RH Passenger and Cargo Compartment 1 1 Lever Action Handle Release Pin H R R185 Fuel Drai...

Page 325: ...er 19 4 Screw Bolt L M TL118 Oil Dipstick Hand Hold LH Engine Oil Level and Filler 1 2 Hinge Camlock Q E TR118 Oil Dipstick Hand Hold RH Engine Oil Level and Filler 1 2 Hinge Camlock Q E T220 Aft Fair...

Page 326: ...and Installation Item No Name Permits Access To Quantity Type Method Ref Figure 8 4 B142 Access Panel Assem bly Center Throttle Interconnect Cable RH Collective 14 Screw L B178 Access Panel Assem bly...

Page 327: ...Left Side Horizontal Stabilizer Mount Fitting Stationary Thruster Mounting 21 Screw L SL3 Outboard Fairing As sembly LH Endplate Vertical Stab Torque Tube Control Rod Electrical Wiring Position Light...

Page 328: ...uel Cell 12 Screw L AL165 Cabin Floor Left Out board Panel Fuel Cell Frangible Valve Wire Harness 76 Screw L AL230 Cabin Floor Left Aft Ac cess Cover Left Aft Fuel Vent Valve Fuel Cell 13 Screw L AL25...

Page 329: ...9G06 012 PR120 PL120 Removal and Installation Item No Name Permits Access To Quantity Type Method Ref Figure 8 4 PL120 Panel Wire Harness Forward Interconnect Panel Relays Ground Modules 9 Camloc U P...

Page 330: ...Assem bly Fan Assembly Fan Driveshaft Cou pling Support Housing Fan Balance Monitor System Magnetic Pickup and Accelerometer 19 Screw L F4 Anti Torque Middle Inlet Duct Assembly Fan Assembly Plenum ai...

Page 331: ...apacities are shown in Table 8 1 A complete listing of servicing materials may be found in the RMM Section 12 00 00 9G12 002 F92 116 4 6 1 2 3 7 8 9 5 10 11 1 ECS AIR CONDITIONER REFRIGERANT 2 ECS AIR...

Page 332: ...5 MIL T 5624 CGSB 3 GP 24Ma AVCAT DERD 2452 DERD 2498 AIR 3404C F 43 F 44 Contains fuel system icing inhibitor FSII For JP 8 MIL T 83133C allows two grades The grade meeting NATO code F 34 has FSII wh...

Page 333: ...ario Canada M8W 1P2 Castrol Specialty Products Div 16715 Von Karman Ave Suite 230 Irvine CA 92714 4918 Castrol U K Ltd Burmah House Pipers Way Swindon Berkshire SN3 1RE England MIL PRF 23699 Mobil Jet...

Page 334: ...g vehicle should be parked a minimum of 20 feet from helicopter during fueling operation At least one fully charged 50 pound CO2 fire extinguisher shall be in the immediate area Before starting fuelin...

Page 335: ...re that the gravity filler port check valve fully opens Do not attempt to refuel helicopter if the lanyard has broken Service fuel cell slowly Secure filler cap after fueling Remove fuel nozzle and gr...

Page 336: ...le folds and clips against the reservoir housing for storage When in use the handle extends through the open access panel providing a convenient means of operation NOTE The following servicing procedu...

Page 337: ...LEVER HAND PUMP OPTIONAL FLUID LEVEL SIGHT GAUGE FILTER BOWL RETURN HYDRAULIC MAINFOLD FLUID LEVEL SIGHT GAUGE COVER FILTER BYPASS INDICATORS FILTER BOWL PRESSURE FLUID TEMP 40 C 95 C FULL REFILL EMP...

Page 338: ...Close oil filler cap Close access panel Ref Figure 8 6 and Figure 8 7 Main Transmission Draining Open access panel Ref Figure 8 6 and Figure 8 7 Remove chip detector Ref RMM Section 63 20 00 Using tr...

Page 339: ...D FULL VIEW ROTATED OIL LEVEL INDICATOR OIL FILLER CHIP DETECTOR HOUSING FILTER BYPASS INDICATOR TRANSMISSION OIL FILL SERVICE WITH MOBIL SHC 626 OIL NOTE 900D1400006 101 TRANSMISSION ONLY TRANSMISSIO...

Page 340: ...l 8 30 Rotor brake The rotor brake reservoir is located on the top forward deck Open right hand forward access door Remove filler cap Using hydraulic fluid fill reservoir to top of sight glass Install...

Page 341: ...OTE This task is typical for left and right hand engine Open main transmission access door Ref Figure 8 6 and Figure 8 7 Remove engine oil filler cap Refill engine oil tank with specified oil in relat...

Page 342: ...LTER CASE VIEW LOOKING AFT CHIP DETECTOR OIL FILTER IMPENDING BYPASS INDICATOR OIL FILLER DIPSTICK F92 121 OIL LEVEL SIGHT GLASS MINIMUM OIL LEVEL OIL FILLER DIPSTICK VIEW ROTATED OIL LEVEL SIGHT GLAS...

Page 343: ...small hand brush Any flammable solvent that may affect material flammability must be removed completely after cleaning Sponge soiled upholstery and trim panels with a mild soap and lukewarm water sol...

Page 344: ...r 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 surfac...

Page 345: ...ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E Handling Servicing and Maintenance Original 8 35 DOOR RELEASE HANDLE DOOR HANDLE GAS STRUT F92 123 DOOR RESTRAINT BALL SOCKET BALL STUD Figure 8 20 Cockpit...

Page 346: ...in Seat Installation Ref Figure 8 21 Align cabin seat assembly with floor anchor plates First engage lower quick disconnect fittings then upper quick disconnect fittings of cabin seat assembly into ma...

Page 347: ...gure 8 22 Copilot Pedals Copilot Pedals Disengaging Ref Figure 8 22 Copilots pedal shaft assemblies can be temporarily stowed in the full forward position Pull up pedal adjustment pins Pull out pedal...

Page 348: ...20 150 180 210 240 270 300 330 SEC MIN 1 2 3 4 5 AREA B AREA C NO ACTION REQUIRED AREA A RECORD IN ENGINE LOG BOOK 2 5 MINUTE RATING AREA B RECORD IN ENGINE LOG BOOK CONTINUOUS OEI AREA C RETURN ENGIN...

Page 349: ...HSI AREA C RETURN ENGINE TO OVERHAUL AREA D DETERMINE CAUSE FOR HUNG START AND CARRY OUT DRY MOTORING RUN PRIOR TO ATTEMPTING A RE START TIME SECONDS MEASURED GAS TEMPERATURE EGT 2 650 760 875 45 AREA...

Page 350: ...240 260 280 300 3 4 5 103 4 AREA B AREA A 97 4 NO ACTION REQUIRED Figure 8 26 Compressor Turbine NG Speed Vs Time 5 MI N 2 5 MI N F92 130A AREA C AREA A AREA B 0 20 30 60 90 120 150 180 210 240 270 30...

Page 351: ...frequency of the following checks These checks and or procedures are to be performed only while aircraft is on the ground ENGINE NP OVERSPEED TEST PROCEDURE F Engine control switches SET BOTH TO IDLE...

Page 352: ...isplay VERIFY 250 PSI MAXIMUM FOR HYD 2 AND 1 000 100 50 PSI FOR HYD 1 F F HYD TEST switch RELEASE AND CHECK HYD 2 CAUTION SEGMENT OFF VSCS CHECK NOTE This functional check may be performed with the e...

Page 353: ...uel boost pump ON F Engine control switch IDLE NOTE Maintain starter operation for desired duration while observing starter limits F Engine control switch OFF F Fuel boost pump OFF NOTE After a wet mo...

Page 354: ...nufacturers publications Ref RMM Section 01 00 00 Use of correct mixture as specified in the PWC Maintenance manual is very important not only when the temperature is below freezing at the time of was...

Page 355: ...e is expected to be below 2 C 36 F between time of washing and the next start Connect cleaning solution or water source to engine wash panel using AN type fittings Ref Figure 8 28 NOTE To prevent prec...

Page 356: ...ission access door Repeat procedure on other engine Once engine wash is complete start and operate engines at idle for at least one minute to completely dry engines RIGHT ENGINE WASH TUBE ASSEMBLY ENG...

Page 357: ...1 Figure 9 8 Fuel Flow AEO 4000 Feet HP ISA 30 C 37 C 9 12 Figure 9 9 Fuel Flow AEO 8000 Feet HP ISA 30 C 29 C 9 13 Figure 9 10 Fuel Flow OEI Sea Level ISA 15 C 9 14 Figure 9 11 Fuel Flow OEI 4000 Fee...

Page 358: ......

Page 359: ...OCKPIT CHECK ELECTRICAL POWER OFF D All cabin doors CHECK D Seat belt and shoulder harness FASTENED D Rotor brake STOWED D Flight instruments CHECK STATIC POSITION SET D Collective friction ON D Colle...

Page 360: ...S AT COMPLETION OF BIT D Fuel quantity display CHECK D DISP display by exception AS DESIRED ENGINE STARTING AUTOMATIC D L BOOST or R BOOST ON CHECK IIDS INDICATIONS EEC MAN indicators OFF D L ENGINE o...

Page 361: ...T SHUTDOWN NORMAL D Collective stick FULL DOWN FRICTION ON D Cyclic stick TRIM TO NEUTRAL D Pedals NEUTRAL D L ENGINE and R ENGINE IDLE D All unnecessary electrical equipment OFF D Heat OFF D Pitot he...

Page 362: ...his data is based on a baseline aircraft with 15 electrical load engine bleeds and air conditioner off Use of Chart Use the charts as illustrated by the example below NOTE The following example uses F...

Page 363: ...rations and Performance Data Original 9 5 F92 131 1 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 LONG RANGE CRUISE 6000 LB 500...

Page 364: ...ations and Performance Data Original 9 6 F92 131 2 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS MCP LIMIT 4000 LB LONG RANGE C...

Page 365: ...ations and Performance Data Original 9 7 F92 131 3 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 MCP LIMIT 4000 LB LONG RANGE C...

Page 366: ...s and Performance Data Original 9 8 F92 132 1 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS 200 250 300 350 400 450 500 550 600 650 700 40 50 60 70 80 90 100 110 120 130 140 150 MCP LIMIT 4000 LB LONG RANG...

Page 367: ...ons and Performance Data Original 9 9 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS F92 132 2 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 MCP LIMIT 4000 LB LONG RANGE CRUI...

Page 368: ...ons and Performance Data Original 9 10 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS F92 132 3 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 MCP LIMIT 4000 LB LONG RANGE CRU...

Page 369: ...ions and Performance Data Original 9 11 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 FUEL FLOW LB HR MCP LIMIT 4000 LB LONG RANGE CRUISE 6000 LB 5000 LB INDICATED AIRS...

Page 370: ...ons and Performance Data Original 9 12 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 FUEL FLOW LB HR MCP LIMIT 4000 LB LONG RANGE CRUISE 6000 LB 5000 LB INDICATED AIRSP...

Page 371: ...ons and Performance Data Original 9 13 200 250 300 350 400 450 500 550 600 40 50 60 70 80 90 100 110 120 130 140 150 FUEL FLOW LB HR MCP LIMIT 4000 LB LONG RANGE CRUISE 6000 LB 5000 LB INDICATED AIRSP...

Page 372: ...206E Additional Operations and Performance Data Original 9 14 F92 134 1 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR VNE 100 KIAS 4000 LB 6000 LB 5000 LB 6250 LB INDICATED AIRSPEED KNOTS...

Page 373: ...206E Additional Operations and Performance Data Original 9 15 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR VNE 100 KIAS 4000 LB 6000 LB 5000 LB 6250 LB INDICATED AIRSPEED KNOTS MCP LIMIT...

Page 374: ...PW 206E Additional Operations and Performance Data Original 9 16 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT 6000 LB F92 134 3 VNE 100...

Page 375: ...6E Additional Operations and Performance Data Original 9 17 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR VNE 100 KIAS 4000 LB 6000 LB 5000 LB 6250 LB INDICATED AIRSPEED KNOTS MCP LIMIT F9...

Page 376: ...h PW 206E Additional Operations and Performance Data Original 9 18 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT F92 135 2 VNE 100 KIAS F...

Page 377: ...h PW 206E Additional Operations and Performance Data Original 9 19 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT F92 135 3 VNE 100 KIAS F...

Page 378: ...th PW 206E Additional Operations and Performance Data Original 9 20 F92 136 1 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT VNE 100 KIAS...

Page 379: ...h PW 206E Additional Operations and Performance Data Original 9 21 F92 136 2 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT VNE 100 KIAS F...

Page 380: ...h PW 206E Additional Operations and Performance Data Original 9 22 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT F92 136 3 VNE 100 KIAS F...

Page 381: ...06E Additional Operations and Performance Data Original 9 23 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR 4000 LB 5000 LB INDICATED AIRSPEED KNOTS MCP LIMIT F92 188 1 VNE 100 KIAS 6000 LB...

Page 382: ...E Additional Operations and Performance Data Original 9 24 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS F92 188 2 VNE 100 KIAS 4000 LB 5000 LB 6000 LB 6250 LB MCP...

Page 383: ...206E Additional Operations and Performance Data Original 9 25 200 250 300 350 400 40 50 60 70 80 90 100 FUEL FLOW LB HR INDICATED AIRSPEED KNOTS MCP LIMIT F92 188 3 VNE 100 KIAS 4000 LB 5000 LB 6000...

Page 384: ...OISE LEVELS The MD900 meets the ICAO Annex 16 Volume 1 Chapter 8 noise requirements for level flight takeoff climb and approach descent profiles at the certified maximum gross weight of 6250 LB MD900...

Page 385: ...s 10 7 Figure 10 3 Collective Stick Switch Panel 10 8 Figure 10 4 Circuit Breakers Console Mounted Typical 10 9 Figure 10 5 Circuit Breakers Baggage Compartment Mounted Typical 10 10 10 7 Operating In...

Page 386: ...35 Figure 10 15 Center of Gravity Envelope for Hoist Operations Below 60 KIAS 10 36 Figure 10 16 Rescue Hoist Controls 10 40 Figure 10 17 Allowable Rescue Hoist Loading Chart 10 44 Figure 10 18 Rescue...

Page 387: ...he Flight Manual Supplemental Data is to be used in conjunction with the basic Flight Manual data and takes precedence over that data when the equipment is installed Be sure to include a review of the...

Page 388: ...eat CSP 900RFM206E 1 Rotor brake CSP 900RFM206E 1 Engine air particle separator filter CSP 900RFM206E 1 Indicates data incorporated into the flight manual Sections I thru IX where appropriate Table 10...

Page 389: ...ge to air conditioning system Low Pressure Switch Activates or deactivates the Freon compressor assembly in a low pressure condition to prevent damage to the air conditioning system Thermal Expansion...

Page 390: ...M CABIN EVAP FAN 3 WAY VALVE RECEIVER DRYER CONDENSER OVBD DRAIN OVERBOARD CONDENSER FAN COMPRESSOR ASSEMBLY LOW PRESSURE SWITCH HIGH PRESSURE SWITCH TXV EVAPORATOR CABIN PASSENGER COMPARTMENT CREW PI...

Page 391: ...sure gas coolant passing through the condenser will notbecome a liquid due to heat retention This will result in a higher than normal pressure in the lines to the evaporator Whenthis condition is dete...

Page 392: ...L HIGH position provides air conditioning at a high setting COOL LOW provides air conditioning at a low setting selected from the center console utility panel assembly IPS HEAT AC VENT PITOT HEAT HYD...

Page 393: ...and landing lights switch while positioning the search light is accomplished by operating the five posi tion search light switch Ref Table 10 3 PART II LIMITATIONS No Change PART III EMERGENCY AND MAL...

Page 394: ...MBLY OR BURNED OUT BULB D Console mounted LND LGT circuit breaker IN REF FIGURE 10 4 D Baggage compartment mounted SRCH LT and HOV SRCH LT circuit breakers IN REF FIGURE 10 5 D Collective stick switch...

Page 395: ...el D D LIGHTS switch to HVR Ref Figure 10 3 CHECK HOVER AND SEARCH LIGHTS ON D D Use search light switch to rotate light left L and right R CHECK OPERATION D D LIGHTS switch to LDG CHECK HOVER LANDING...

Page 396: ...EVAP VENT EVAP COMP PITOT HEAT2 ATT GYRO2 HOV SRCH LT CNDSR FAN 2 IIDS TRAK STB CFU AV FAN IPS ATT GYRO1 LAND LGT CNDSR FAN 1 ADF2 RADAR RT RADAR IND RADAR INVTR RAD ALT MKR BCN COM2 XPNDR 2 DIR GYRO...

Page 397: ...ry bus power to the search light through the hover and landing light relays Movement of the search light is accomplished by actuating the search light switch located on the collective stick switch pan...

Page 398: ......

Page 399: ...nts for the bridle allow the flight crew to install or remove the hook assembly Quick disconnects for the electric and mechanical release cables are located on the bottom of the fuselage near the forw...

Page 400: ...ions Maximum weight on the hook is 3000 LBS unless placarded otherwise Ref Figure 10 9 Airspeed Limitations With no load on hook maximum VNE is 90 KIAS With load on hook maximum VNE is 100 KIAS Ref Fi...

Page 401: ...202 204 206 7000 6500 6000 5500 5000 4500 4000 3500 3000 FUSELAGE STATION IN WEIGHT POUNDS F90 055A 208 NORMAL CG LIMITS CARGO HOOK CG LIMITS 6250LBS 7000 6500 6000 5500 5000 4500 4000 3500 3000 LATE...

Page 402: ...tigue Check for fraying wear or any other form of damage to the cable bridle assembly Inspect electrical release and load indicating wire harness and connectors for gener6 al condition and security Ex...

Page 403: ...is adequate clearance between the sling load and any obstacles along the takeoff flightpath Activate cargo release switch on cyclic stick to release cargo Check CARGO HOOK OPEN advisory on IIDS alpha...

Page 404: ...GO HOOK LOAD INDICATOR ELECTRICAL CONNECTOR MANUAL RELEASE CABLE CONNECTION ELECTRICAL RELEASE CONNECTOR AFT SADDLE CLAMP FWD SADDLE CLAMP QUICK RELEASE PIN SEE NOTE PIN LINK CABLE LOAD BEAM QUICK REL...

Page 405: ...12 lbs The following table of Cargo Hook Loads may be used by the operator to assist in determining the helicopter center of gravity Cargo Weight lb Moment 100 in lb Cargo Weight lb Moment 100 in lb 1...

Page 406: ...ks Connect cargo hook electrical connector load indicator electrical connector and mechanical release control cable connector Repeat procedure for aft link assembly attachment Perform cargo hook prefl...

Page 407: ...n or snow The windscreen washers if installed provide pressurized washer fluid to the wind screen through spray nozzles The washer pump and reservoir are located in the battery compartment There are n...

Page 408: ...refer to wiper speed Select the speed appropriate for weather conditions Windscreen washer if installed Preflight Check Check washer reservoir fluid level On dry windscreen Press and hold the WASHER...

Page 409: ...Washer reservoir full water alcohol mixture 4 8 4 3 82 7 82 7 394 356 PART VIII HANDLING SERVICING AND MAINTENANCE Servicing Materials Windscreen Washer Fluid Specification Material Manufacturer Wash...

Page 410: ......

Page 411: ...T I GENERAL The MD900 supplemental fuel system option adds a transfer type auxiliary fuel tank located below the baggage compartment floor Refer to Part VII for system description PART II LIMITATIONS...

Page 412: ...rmal cruise Transferring fuel to the main tank may be accomplished once main tank indicated fuel quantity is at or less than approximately 500 LB in normal ground attitude or approximately 700 LB in n...

Page 413: ...Original 10 27 F90 155A ON OFF FUEL TRANSFER INDICATOR LIGHT FUEL TRANSFER SWITCH AUXILIARY FUEL QUANTITY GAUGE GAUGE SWITCH AND INDICATOR LIGHT SUPPLEMENTAL FUEL SYSTEM USE MAIN FUEL DOWN TO 700 LBS...

Page 414: ...STATION ARM MOMENT IN LB Basic Weight 3512 4 738045 Pilot 185 0 130 70 24180 Copilot Passenger 185 0 130 70 24180 Passenger Rear Facing R H 175 0 173 0 30275 Passenger Rear Facing L H 175 0 173 0 302...

Page 415: ...80 242 3 19387 2 0 140 100 242 9 24294 2 0 200 120 243 4 29210 2 0 240 140 243 8 34133 2 0 280 160 244 1 39062 2 0 320 180 244 4 44000 2 0 360 200 244 8 48951 2 0 400 Table 10 5 Fuel Loading Table Jet...

Page 416: ...FUEL WEIGHT LB JET B 6 5 LB GAL FUSELAGE STATION INCHES 238 0 238 5 239 0 239 5 240 0 240 5 241 0 241 5 242 0 242 5 243 0 243 5 244 0 244 5 245 0 210 200 190 180 170 160 150 140 130 120 110 100 90 80...

Page 417: ...the main tank until the fuel remaining in the main tank is less than approximately 500 LB in normal ground attitude or approximately 700 LB in normal cruise attitude The level control valve will shut...

Page 418: ...ILL PORT AFT RH VENT LINE FLAME ARRESTOR AFT VENT FAIRING AUX FUEL PORT VENT ROLLOVER VALVE CABIN FLOOR REF MAIN FUEL TANK REF LEVEL CONTROL VALVE STA 230 5 BULKHEAD CHECK VALVE FUEL TRANSFER LINE BAG...

Page 419: ...900RFM206E 1 ROTORCRAFT FLIGHT MANUAL MD900 With PW 206E FAA Approved Original 10 33 10 34 blank PART VIII HANDLING SERVICING AND MAINTENANCE Fuel additives Anti icing additives if required must be ad...

Page 420: ......

Page 421: ...under appropriate airworthiness and or oper ating rules for external loads Minimum flight crew Pilot when conducting operations with hoist stowed Pilot and hoist operator when conducting hoist operati...

Page 422: ...tions Maximum load on hoist is 600 LB Maximum permissible cable deflection is 15 with respect to the aircraft vertical axis During normal flight operations and airspeeds above 60 KIAS the cable hook m...

Page 423: ...n generator load within limits Allowing a GENERATOR HIGH LOAD condition to exist will result in the operating generator going off line ADVISORY INDICATIONS Indications Green indicator light located on...

Page 424: ...s of swivel and latch CHECK D Hoist support tube CHECK MOUNTING D Hoist strut CHECK MOUNTING AND QUICK RELEASE PIN D Pendant control electrical connection CHECK D HOIST PWR and HOIST CUT circuit break...

Page 425: ...um D D Hoist arming switch OFF D Electrical Master Panel D D Power switch OFF Hoist operation Hoist operator must wear appropriate safety gear safety harness and have voice communications with the pil...

Page 426: ...E PAYOUT DISPLAY ICS CONTROL SWITCH HOIST OPERATOR S CONTROL PENDANT ASSEMBLY ON OFF HOIST PAYOUT DIRECTION SPEED CONTROL HOIST ARMING SWITCH COLLECTIVE CONTROL MODULE REF INSTRUMENT PANEL REF DN UP P...

Page 427: ...hoist load changes with gross weight and aircraft CG Refer to Figure 10 17 to determine maximum allowable hoist load ITEM WEIGHT STATION ARM MOMENT ITEM WEIGHT Lateral Longitudinal Lateral Longitudina...

Page 428: ...0 19 00 3800 Fuel 700 0 00 0 Gross Weight 4509 6 8446 Calculation of Lateral CG CG at Gross Weight Moment at Gross Weight 8446 1 90 Gross Weight 4509 6 1 90 EXAMPLE II Lateral CG Determination Destina...

Page 429: ...ist Load ITEM WEIGHT LB STATION ARM MOMENT IN LB Basic Weight 3272 8 1465 0 Hoist Installation 136 8 55 60 7611 0 Pilot 200 0 15 85 3170 0 Hoist Operator R H step 200 0 35 00 7000 0 Hoist load 250 0 5...

Page 430: ...GATION CG IN WITHOUT HOIST LOAD HELICOPTER GROSS WEIGHT LB WITHOUT HOIST LOAD Figure 10 17 Allowable Rescue Hoist Loading Chart Use of chart Use Figure 10 17 to determine the maximum hoist load for th...

Page 431: ...tch located on the collective control module With the load selection switch set at 250 cable speed is 225 feet per minute With the load selection switch set at 600 cable speed is 100 feet per minute R...

Page 432: ...ginal 10 46 SUPPORT TUBE STRUT CONTROL PENDANT VARIABLE SPEED CONTROLLER HOIST SUPPORT ASSEMBLY ROTATED HOOK F92 177 HOIST ASSEMBLY FAIRING REMOVED FAIRING MID SKID GUARD AFT INBOARD WHITE STRIPE 15 1...

Page 433: ...10 6 Servicing Materials Specification Material Manufacturer Hoist assembly MIL L 7808 Stauffer Jet I Stauffer Chemical Co 380 Madison Avenue New York NY 10017 American PQ Lubricant 6899 American Oil...

Page 434: ......

Page 435: ...pilot to direct a charge of fire extinguishing agent into the designated fire zone of each engine There is no fire extinguishing system for the transmission area PART II LIMITATIONS No change PART II...

Page 436: ...d with dual outlet ports a pressure gauge with electrical low pressure warning signal to IIDS filler port and thermal relief valve The outlets ports are fitted with electrically discharged explosive s...

Page 437: ...EFT SIDE REF ENGINE DECK DISCHARGE TUBE OUTLET PORT DISCHARGE TUBE OUTLET PORT CROSS FLOW TUBES FIRE BOTTLE ASSEMBLY BLUE PORT ALTERNATE CARTRIDGE RED PORT PRIMARY CARTRIDGE PRESSURE GAUGE FILLER PORT...

Page 438: ......

Page 439: ...4 Weight Limitations 11 3 Figure 11 4 Longitudinal Center of Gravity Envelope 11 3 11 5 Performance Data 11 4 Figure 11 5 Height Velocity Diagram 11 4 Figure 11 6 Single Engine Rate of Climb and Desce...

Page 440: ......

Page 441: ...S 11 1 GENERAL By observing the limitations and performance data described in this section pilots may operate at internal gross weights from above 6250 pounds up to and including 6500 pounds Compatibi...

Page 442: ...SURE ALTITUDE FEET FREE AIR TEMPERATURE C 36 Figure 11 1 Ambient Temperature Envelope Critical wind azimuth in hover Refer to Figure 1 1 2 120 135 270 190 80 A 15 KTS 17 KTS 17 KTS CRITICAL AZIMUTH B...

Page 443: ...AT GROSS WEIGHTS FROM 6250 TO 6500 LBS VNE CARD F927 112 Figure 11 3 VNE Placard 11 4 WEIGHT LIMITATIONS Maximum gross weight 6500 lbs CG Limits Lateral CG limit is 2 inches Ensure helicopter CG and w...

Page 444: ...H airspeed is for demonstrating compliance to 14 CFR Part 36 Appendix H only and does not imply approval to exceed established VNE airspeeds Performance charts Rate of climb charts Ref Section V for i...

Page 445: ...11 5 10 C 30 C 40 C 50 C MAXIMUM OAT LIMIT OAT RATE OF CLIMB DESCENT AT VY FT MIN 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 PRESSURE ALTITUDE FEET 400 300 200 100 0 100 200 300 400 500 10...

Page 446: ...Original 11 6 F90 167 1 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 PRESSURE ALTITUDE FEET RATE OF CLIMB AT VY FT MIN OAT 30 C 36 C 20 C 10 C 0 C 10 C 20 C 30 C 40 C 400 600 800 1000 1200 14...

Page 447: ...TUDE FEET 0AT C MAXIMUM INTERNAL GROSS WEIGHT HOVER CAPABILITY IGE HEATER ON AND AC OFF 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 36 30 20 10 0 10 20 30 40 50 40 10000 6500 LBS 5000 FT HD LIMIT 6...

Page 448: ...DE FEET 0AT C MAXIMUM INTERNAL GROSS WEIGHT HOVER CAPABILITY OGE HEATER ON AND AC OFF 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 36 30 20 10 0 10 20 30 40 50 40 10000 6500 LBS 5000 FT HD LIMIT 630...

Page 449: ...PRESSURE ALTITUDE FEET 0AT C MAXIMUM INTERNAL GROSS WEIGHT HOVER CAPABILITY IGE HEATER OFF AND AC ON 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 36 30 20 10 0 10 20 30 40 50 40 10000 6500 LBS 5000...

Page 450: ...ALTITUDE FEET 0AT C MAXIMUM INTERNAL GROSS WEIGHT HOVER CAPABILITY OGE HEATER ON AND AC OFF 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 36 30 20 10 0 10 20 30 40 50 40 10000 6500 LBS 5000 FT HD LI...

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