MD Helicopters MD 520N Flight Manual

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THIS IS A COMPLETE REPRINT OF

CSP–520N–1

AND IS CURRENT THROUGH REISSUE #1,

INCLUDING REVISIONS 1 AND 2

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Summary of Contents for MD Helicopters MD 520N

Page 1 THIS IS A COMPLETE REPRINT OF CSP–520N–1 AND IS CURRENT THROUGH REISSUE #1, INCLUDING REVISIONS 1 AND 2...
Page 3 MD 520N Cover 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: _________________ F05–000...
Page 5 CSP–520N–1 MD 520N Title Page FAA APPROVED ROTORCRAFT FLIGHT MANUAL Type Certificate No. H3WE Approved By_____________________________________ Manager, Flight Test Branch Los Angeles Aircraft Certification Office Transport Airplane Directorate Original Approval Date: 12 September 1991 Reissue #1: _______________________________________ THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL CONSISTS OF THE FOLLOWING SECTIONS.
Page 6 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LOG OF REVISIONS BY DATE FAA / NON–FAA REVISIONS REVISION DATE/NUMBER Original ..12 September 1991 Revision 1 ..1 April 1992 Revision 2 .
Page 7 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 APPROVING AUTHORITIES Centro Técnico Aeroespacial (CTA) This Rotorcraft Flight Manual is approved by the FAA on behalf of Centro Técnico Aeroes- pacial for Brazilian registered rotorcrafts in accordance with the ‘‘Regulamentos Brasileiros de Homologação Aeronáutica’’ (RBHA) Part 21, Section 21.29.
Page 9 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 TABLE OF CONTENTS PARAGRAPH PAGE Cover ..............
Page 10 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 PARAGRAPH PAGE 2−10. Fuel System Limitations ..........
Page 11 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 PARAGRAPH PAGE 4−10. Doors Off Flight ............
Page 12 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 PARAGRAPH PAGE 7−5. Moving and Towing Helicopter .........
Page 13 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 SUMMARY OF REVISIONS TO THE ROTORCRAFT FLIGHT MANUAL NOTE: Revisions are listed below by number with appropriate remarks. Section II pages marked [C]* indicate FAA approved color pages. Black–and–white reproductions of color pages are not considered to be “FAA Approved”.
Page 14 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER Cover − − − − − − − − Original FRONT F−i Original − − − − − − − −...
Page 15 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 1−13 − − − − − − − − Original 1−14 − − − − − − − −...
Page 16 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 3−1 Original − − − − − − − − 3−2 Original − − − − − − − −...
Page 17 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 4−4 Revision 1 − − − − − − − − 4−5 Revision 1 − − − − − − − −...
Page 18 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 5−5 Original − − − − − − − − 5−6 Original − − − − − − − −...
Page 19 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 6−14 − − − − − − − − Original 6−15 − − − − − − − −...
Page 20 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 8−i/(8−ii blank) − − − − − − − − Original VIII 8−1/(8−2 blank) − − − − − − − −...
Page 21 Table 1−2. Fuel System: Optional Self−Sealing Fuel Tanks ....1−14 Figure 1−1. MD 520N Principal Dimensions − Standard Landing Gear ..1−15 1−15. Conversion Charts and Tables .
Page 23 Refer to Section IX for Optional Equipment. MDHI optional equipment items and STC items which are FAA approved for the MD 520N may be installed and used. Original 1–1...
Page 24 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–5. PILOT’S BRIEFING Prior to flight, passengers should be briefed on the following. Approach and depart the rotorcraft from the front in full view of the pilot, being aware of the main rotor.
Page 25 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General SECTION III − EMERGENCY AND MALFUNCTION PROCEDURES (FAA Approved) Problems which could be encountered in flight are defined and the proce dures necessary to cope with or alleviate them are discussed. The data is recommended by MDHI.
Page 26 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–7. METHOD OF PRESENTATION General information in the various sections is provided in narrative form. Oth er information is given in step−by−step procedures, graphs, charts, or tabular form. The information in the step−by−step procedure is presented in the imperative mode;...
Page 27 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General mand. However, the nature of the specific problem or malfunction may dictate termination of the flight before reaching the destination. 1–9. ABBREVIATIONS Extend; External Air Conditioner Fahrenheit Above Ground Level Federal Aviation Alternate;...
Page 28 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Imperial INST Instrument Outside Air Temperature Inches Out of Ground Effect INST(R) Instrument IVSI Instantaneous Vertical Panel Speed Indicator POSN Position Primary Kilogram PRESS Pressure KCAS Knots Calibrated Airspeed Pounds per Square Inch...
Page 29 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Never Exceed Speed Water Line Versus Best Rate of Climb Speed XMSN Transmission XPNDR Transponder U.S. United States YSAS Yaw Stability Augmentation System 1–10. TECHNICAL PUBLICATIONS A file of technical publications is available to aid in obtaining maximum utili zation of your rotorcraft.
Page 30 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General The following publications are available. Pilot’s Flight Manual (CSP−520N−1). Handbook of Maintenance Instructions (HMI) Servicing and Maintenance Instruments − Electrical − Avionics Component Maintenance Manual (CMM) Structural Repair Manual (SRM) Illustrated Parts Catalog (IPC)
Page 31 General 1–11. DESIGN AND CONSTRUCTION The MD 520N helicopter is a 5 place, turbine powered, rotary−wing aircraft constructed primarily of aluminum alloy while the tailboom and thruster are primarily a graphite composite. The main rotor is a fully articulated five−...
Page 32 Helicopter interior: The standard MD 520N requires a minimum crew of one pilot seated on the left side of the cockpit. The passengers sit to the right, abreast of the pilot. Seat belts are provided for all positions.
Page 33 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Torque is transmitted independently to the rotor through the main rotor drive shaft. Lifting loads are prevented from being imposed onto the main transmission eliminating thrust loading of transmission parts. Anti Torque System: The NOTAR system is an anti−torque system made up of an enclosed fan...
Page 34 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–12. ELECTRICAL SYSTEM The 520N electrical system incorporates a generic electrical wire harness that is common with other current production MD500 series aircraft (369E & 369FF) and includes wiring for common optional equipment kits and future growth.
Page 35 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–13. AUTO REIGNITION SYSTEM The automatic reignition system provides automatic actuation of the ignition exciter in the event that power is lost as a result of engine flameout. The system senses signals from the engine power out warning unit and con sists of a indicator light (RE IGN P RST) on the instrument panel, a RE−IGN...
Page 36 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–14. CAPACITIES AND DIMENSIONS Table 1–1. Fuel System: Standard Non Self–Sealing Fuel Tanks Imp. U.S. Pounds/ Fuel Type Liters Kilograms Jet−A Usable 51.7 62.1 421.9/191.4 Unusable 13.1/5.9 Total 53.3 64.0 435.0/197.3 Jet−B Usable 51.7...
Page 37 ADD 0.87 FEET TO ALL VERTICAL DIMENSIONS 31.39 ft (9.6m) 24.9 ft (7.6m) 8.8 ft. (2.7m) 7.7 ft 7.7 ft 6.9 ft (2.3m) (2.3m) (2.1m) 1.4 ft F05−001 (0.4m) Figure 1–1. MD 520N Principal Dimensions – Standard Landing Gear Original 1–15...
Page 38 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General 1–15. CONVERSION CHARTS AND TABLES EXAMPLE: CONVERT 100 KNOTS TO MPH AND TO KM/HR: ENTER CHART AT 100 KNOTS AND FOLLOW ARROW TO SLOPING LINE. TO FIND MPH, MOVE LEFT AND READ 115 MPH.
Page 39 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General TEMPERATURE ° ° EXAMPLE: CONVERT °F TO °C KNOWN: TEMPERATURE = 50° F METHOD: ENTER AT 50° F READ 10° C ACROSS ON °C SCALE METHOD MAY BE REVERSED TO FIND ° F WHEN ° C IS KNOWN –10...
Page 40 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Table 1–3. Liquid Measure – U.S. Gallons to Liters U.S. Liters Liters Liters Liters Liters Liters Liters Liters Liters Liters Gallons – 3.785 7.571 11.356 15.142 18.927 22.713 26.498 30.283 34.069 37.854 41.640...
Page 41 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Table 1–5. Linear Measure – Feet to Meters Feet Meters Meters Meters Meters Meters Meters Meters Meters Meters Meters – 0.305 0.610 0.914 1.219 1.524 1.829 2.134 2.438 2.743 3.048 3.353 3.658 3.962...
Page 42 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General KNOTS METERS/SEC EXAMPLE CONVERT KNOTS TO METERS/SEC KNOWN: WIND SPEED = 25 KT METHOD: ENTER CHART AT 25 KT READ APPROXIMATELY 13 METERS/SEC ACROSS ON METERS/SEC SCALE METHOD MAY BE REVERSED TO FIND KNOTS WHEN METERS/SEC ARE KNOWN F03–005...
Page 43 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General EXAMPLE 1: 29.44 IN. HG = 997 MBAR EXAMPLE 2: 30.18 IN. HG = 1022 MBAR 29.5 30.5 31.1 29.4 30.4 31.0 29.3 30.3 30.9 29.2 30.2 30.8 29.1 30.1 30.7 29.0 30.0...
Page 44 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 General Table 1–7. Standard Atmosphere Table Standard Sea Level Conditions: Temperature: 59°F (15°C) Pressure: 29.921 in. Hg (1013.25 mbar) Density: 0.0023769 slugs/ft (1.225 kg/m TEMPERATURE ALTITUDE ALTITUDE DENSITY DENSITY PRESSURE PRESSURE PRESSURE PRESSURE...
Page 45 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations E C T I O N IMITATIONS TABLE OF CONTENTS PARAGRAPH PAGE 2−1. Flight Restrictions ........... .
Page 47 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations SECTION II LIMITATIONS 2–1. FLIGHT RESTRICTIONS Approved as a five place (maximum) helicopter. Flight crew position: The minimum flight crew consists of one pilot operating the helicopter from the left seat. The right crew seat may be used for an additional pilot when the approved dual controls are installed.
Page 48 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations Flight with center front seat occupied is approved under the following conditions. Dual controls removed. Center location seatback and seat cushion installed and secured. Seat belt(s) and shoulder harness(es) installed and operable.
Page 49 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–4. WEIGHT LIMITATIONS Maximum gross weight: 3350 lbs. on the landing gear. Minimum flying gross weight: 1796 lbs. Cargo deck capacity: 1300 lbs. (not to exceed 115 lbs. per square foot). Utility stowage compartment: Maximum weight in the utility stowage compartment is 50 pounds.
Page 50 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–5. ROTOR BRAKE LIMITATIONS (IF INSTALLED) The rotor brake must be in the stowed position prior to engine starting. The rotor brake may be applied after engine shutdown with the rotor at or be low 195 RPM.
Page 51 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–7. POWERPLANT LIMITATIONS ALLISON 250–C20R/2 Engine torque limits: Maximum takeoff power (5 minute): 101.8 psi torque Maximum continuous: 89.8 psi torque Transient torque limits: 101.8 to 112.2 psi torque (red dot ton torque indicator) for 10 seconds at...
Page 52 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations Power Turbine (N ) speed limits: Ç Ç Ç Ç Ç Ç Ç É É É É É É É É É É É É É É É Ç Ç Ç Ç Ç Ç Ç...
Page 53 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–9. STARTER LIMITATIONS If ignition is not attained: 1 minute on, 1 minute off; 1 minute on, 23 minutes off; 2–10. FUEL SYSTEM LIMITATIONS Fuel Specifications: Fuel Specifications: For additional information on fuels, refer to the appropriate Rolls Royce Opera tion and Maintenance Manual.
Page 54 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations Emergency Aviation Gasoline MIL−G−5572E. MIL–G–5572 aviation gasolines containing Tri–Cresyl–Phosphate CAUTION (TCP) additives shall not be used. Use of MIL–G–5572E gasolines is limited to a maximum of 6 hours of operation per engine overhaul period and operation within safe conditions.
Page 55 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations FUEL TEMPERATURE ~ DEG C É É É É É É É É É É É É É É É É É É É É É É É 5,000 16,000 É É É É É É É É É É É É É É É É É É É É É É É...
Page 56 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–11. INSTRUMENTATION YELLOW GREEN YELLOW INDICATES CAUTIONARY RED INDICATES MAXIMUM GREEN INDICATES NORMAL OPERATING RANGE. AND MINIMUM OPERATING OPERATING RANGE. LIMITS; THE EDGE OF A RED LINE IS THE LIMITING VAL- UE; THE POINTER SHOULD...
Page 57 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations DUAL TACHOMETER (FACE SHOWN TWICE FOR CLARITY) ROTOR RPM N 2 RPM TACHOMETER 99 AND 100 % 59 AND 105% 410 AND 508 RPM 99 TO 100% 64 TO 105% 410 TO 508 RPM 106.5%...
Page 58 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–12. V PLACARDS Description: The V placards provide the pilot with a method to determine the maxi mum indicated airspeed allowed for various gross weight, pressure altitude and OAT combinations during powered or autorotative flight.
Page 59 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations When operating at altitudes and/or temperatures that fall between those de picted on the placard, linearly interpolate between pressure altitude and temperature to determine the appropriate V (Refer to example 2). If un...
Page 60 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2200 OR LESS ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 21 KTS (87K MIN); DO NOT EXCEED CHART V...
Page 61 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2351 TO 2500 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 21 KTS (90K MIN); DO NOT EXCEED CHART V...
Page 62 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2651 TO 2850 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 21 KTS (94K MIN); DO NOT EXCEED CHART V...
Page 63 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 3101 TO 3350 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 21 KTS (96K MIN); DO NOT EXCEED CHART V...
Page 64 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Limitations 2–13. PLACARDS AND DECALS Minimum N Speed Starting Recommendations OAT, °C –18 AND BELOW –18 TO 7 7 AND ABOVE THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL.
Page 65 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures I I I E C T I O N MERGENCY AND ALFUNCTION ROCEDURES TABLE OF CONTENTS PARAGRAPH PAGE 3−1. General ............. .
Page 66 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures PARAGRAPH PAGE One Way Lock Failure ..........
Page 67 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures SECTION III EMERGENCY AND MALFUNCTION PROCEDURES 3–1. GENERAL The procedures contained in this section are recommendations to be followed in the event of an emergency or malfunction that may potentially affect the safety of the aircrew, passengers, aircraft, or personnel on the ground.
Page 68 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–2. WARNING AND CAUTION INDICATORS Warning and caution indicators are located at the top of the instrument panel (Ref. Figure 3−1). A red warning or yellow caution indicator will illuminate and in some cases, an audible warning will sound announcing a failure or malfunction.
Page 69 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–3. ENGINE FAILURE COMPLETE POWER LOSS ENGINE Indications: Red warning indicator ON and audible warning in headset. Left yaw (due to a reduction in torque) Drop in engine speed.
Page 70 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures The maximum glide distance with power off will be attained at 80 KIAS and 410 N Glide distances attained during an actual engine out autorotation may be less than...
Page 71 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Procedures: Engine Failure − Above 12 Feet and Below 500 Feet AGL The Height − Velocity Diagram (Ref. Section V) depicts the combinations of air speeds vs. altitudes wherein a successful autorotation landing can be made in the event of an engine failure.
Page 72 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–4. AIR RESTART – ENGINE Because the exact cause of engine failure cannot be determined in flight, the decision to attempt a restart will depend on aircraft altitude, time available, rate of descent, and potential landing areas.
Page 73 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–5. LOW ROTOR SPEED ENGINE Indications: Red warning indicator ON and audible warning in headset. Drop in rotor RPM. Change in noise level. NOTE : The LOW ROTOR warning is activated when N falls below 453.
Page 74 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Level aircraft and apply full collective pitch as contact is made with the water. When aircraft begins to roll, lower collective to full down to minimize blades skipping off the water.
Page 75 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–7. FIRE The safety of the helicopter occupants is the primary consideration when a fire occurs. Therefore, if airborne, it is imperative that the pilot maintain control of the aircraft and land immediately. If the fire occurs on the ground or upon landing from an inflight fire, it is essential that the engine be shut down, crew and passengers evacuated and fire fighting begun immediately.
Page 76 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Procedures: Aircraft Evacuation A thorough preflight passenger briefing is essential for a quick and safe evacuation of passengers and crew when fire is involved. How to release seat belts, the opening of doors, the proper exiting of the helicopter keeping head and hands low to avoid the main rotor, are all critical to insure the safety of passengers and crew.
Page 77 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: Engine compartment fire Procedures: Twistgrip CUTOFF Fuel shutoff valve PULL TO CLOSE BAT/EXT switch Passengers/crew EVACUATE IF TIME AND SITUATION PERMIT: Rotor brake (if installed) APPLY Secure area...
Page 78 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: At high altitude (AGL) Procedures: Prevailing circumstances such as altitude (AGL), available landing areas, and confirmation of engine fire must be considered in order to determine whether to execute a power−on approach, as described for low altitude (AGL) fires, or a power off autorotational descent to the ground.
Page 79 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: In flight Procedures: Land immediately POWER ON APPROACH AND LANDING WITHOUT DELAY Air vents VENTILATE CABIN AS NECESSARY Twistgrip CUTOFF–AS SOON AS HELICOPTER IS ON GROUND BAT/EXT switch...
Page 80 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–8. ENGINE FUEL CONTROL SYSTEM MALFUNCTIONS FUEL CONTROL OR POWER TURBINE GOVERNOR FAILURE Indications: Failure is indicated by an instrument needle fluctuation. A rise or drop of: Torque Conditions: Failure Producing an Overspeed.
Page 81 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: Failure Producing an Underspeed: Indications: decaying. Possible left yaw. Possible low rotor warning indication. Procedures: Lower collective to maintain rotor RPM in the green (410−508) and at tempt level flight at 60 knots IAS.
Page 82 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–9. OTHER ENGINE CAUTION INDICATIONS ENGINE CHIP DETECTOR ENGINE Indications: Yellow indicator ON. CHIPS Conditions: Metal contamination of oil. Procedures: Land as soon as possible. LOW ENGINE OIL PRESSURE Indications: Oil pressure decreasing below normal operating range (Ref.
Page 83 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–10. MAIN ROTOR AND AFT TRANSMISSION MALFUNCTIONS M/R TRANSMISSION OIL PRESSURE XMSN Indications: Red indicator ON. PRESS Conditions: Transmission oil pressure low. Procedures: Land as soon as possible. M/R TRANSMISSION OIL TEMPERATURE...
Page 84 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–11. FLIGHT CONTROL MALFUNCTIONS ANTI−TORQUE FAILURE Different types of failure require slightly different techniques for optimum suc cess in recovery. Therefore, it is not possible to provide a standardized solution for an anti−torque emergency.
Page 85 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: Complete loss of thrust − at a hover Indications: Failure is normally indicated by an uncommanded right turn. Procedures: Place the twistgrip in the ground idle position and perform a hovering autorotation.
Page 86 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures YSAS MALFUNCTION Indications: YSAS malfunctions are normally indicated by a one inch shift in pedal trim position or aircraft oscillations in the yaw axis. Procedures: If YSAS malfunction is suspected, turn off the YSAS switch.
Page 87 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures CYCLIC TRIM FAILURE Indications: Inability to reduce cyclic forces with the cyclic trim switch. The failure will be one of the following types. Control of the helicopter is the primary consideration of a pilot WARNING confronted with any type of trim motor or switch malfunction.
Page 88 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures Conditions: Runaway trim Indications: An uncommanded longitudinal or lateral cyclic trim actuation. The cyclic may move to a full travel position or some intermediate position resulting in cyclic forces up to the maximum. Uncommanded movement can occur after cyclic trim switch actuation or as a result of an electrical short.
Page 89 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–12. ABNORMAL VIBRATIONS Indications: Sudden, unusual or excessive vibrations occurring during flight. Conditions: The onset of unusual or excessive vibrations in the helicopter may be an indication of problems in the rotor or drive train systems.
Page 90 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures FUEL LOW FUEL Indications: Yellow indicator ON when approximately 35 pounds of fuel LEVEL (22.5 LBS usable) remain in fuel tank. Never use the FUEL LEVEL LOW light as a working indication of CAUTION fuel quantity.
Page 91 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–14. ELECTRICAL SYSTEM MALFUNCTIONS BATTERY OVERTEMPERATURE Indications: Red indicator ON. TEMP 160° Conditions: Battery overtemperature at 160°F (71°C) or above. Procedures: Battery switch: OFF. NOTE : The battery hi–temp relay removes the battery from the DC electrical bus when battery temperature reaches 160°F.
Page 92 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures GENERATOR MALFUNCTION Indications: Yellow indicator ON, and ammeter indicating zero. Generator (GEN) switch tripped to OFF (‘‘early generic’’ configuration only) NOTE : See Sections I and IV to determine which version of the electrical system is installed in the aircraft.
Page 93 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–15. OTHER MALFUNCTIONS ENGINE AIR PARTICLE SEPARATOR FILTER CLOGGED (IF INSTALLED) Indications: Yellow indicator ON. FILTER CLOGGED Conditions: A predetermined pressure differential has been reached across the engine air inlet.
Page 94 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Emergency and Malfunction Procedures 3–16. EMERGENCY EGRESS Pilot compartment doors: Pilot doors function as primary and emergency exits. Cabin doors: Passenger doors function as primary and emergency exits. EXIT OPEN LOCK PILOT COMPARTMENT DOOR LH (TYPICAL) PILOT/PASSENGER COMPARTMENT DOOR EXIT F03–012...
Page 95 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Normal Procedures E C T I O N ORMAL ROCEDURES TABLE OF CONTENTS PARAGRAPH PAGE 4−1. Preflight Requirements ..........
Page 97 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures SECTION IV NORMAL PROCEDURES 4-1. PREFLIGHT REQUIREMENTS NOTE : The checks described in this Section apply to the standard configuration MD 520N and do not include certain optional equipment items. Preflight checks for optional equipment items may be found in Section IX of this manual.
Page 98 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures F05−010 Figure 4-1. Pilot’s Preflight Guide FAA Approved Original...
Page 99 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures DAILY PREFLIGHT CHECKS PRELIMINARY CHECKS CHECK FOR Fuel cell drain valve − take sample (Start pump OFF) CONTAMINANTS CHECK FOR Anti−ice fuel filter drain valve (if installed) take sample CONTAMINANTS (Start pump ON) Do not open anti-ice fuel filter drain valve unless start pump is ON.
Page 100 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures FUSELAGE - RH SIDE CHECK Skid, strut fairings, strut cuffs CHECK Position light, and/or skid tip NO OBSTRUCTIONS Fuel tank vent CHECK Fuselage skin NO OBSTRUCTIONS Right side static port CHECK...
Page 101 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures NO OBSTRUCTIONS NOTAR fan inlet SECURED NOTAR inlet screen SECURED All inspections doors/panels CIRCULATION CONTROL TAILBOOM AND DIRECT JET THRUSTER NO DAMAGE Tailboom: ALLOWED CHECK CONDITION Tailboom fairing AND SECURITY NO OBSTRUCTIONS...
Page 102 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures ENGINE COMPARTMENT CHECK Engine mounts, mounting pads, and firewalls CHECK Landing gear attach points, rear dampers (leaks and inflation) CHECK Engine oil, air, and fuel lines CHECK Scavenge oil filter bypass indicator...
Page 103 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures FUSELAGE - UNDERSIDE CHECK Fuselage skin NO OBSTRUCTIONS Fuel tank and other vents CHECK (REF. Cargo Hook (if installed) SECTION IX) CHECK Antennas INTERIOR AFT COMPARTMENT CHECK Impeller belt CHECK Fuel vapor return line...
Page 104 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures PREFLIGHT CHECKS Perform these checks prior to subsequent flights of the same day. CHECK Fluid levels CHECK Engine compartment − fluid leaks and bypass indicators CHECK Air inlet screens/particle separator CHECK...
Page 105 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures ENGINE OIL TEMPERATURE ALTIMETER INDICATOR AIRSPEED INDICATOR ENGINE OIL PRESSURE INDICATOR FUEL PLACARDS QUANTITY INDICATOR AMMETER CLOCK DUAL TACHOMETER TORQUE INDICATOR TURBINE OUTLET TEMPERATURE FUEL PULL VALVE (TOT) INDICATOR FRESH AIR Ç...
Page 106 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures SWITCH HOUSING SWITCH HOUSING LANDING LIGHT SWITCH IDLE RING COPILOT’S TWIST GRIP PILOT’S THROTTLE GOVERNOR TWIST GRIP INCREASE/DECREASE SWITCH THROTTLE TWIST GRIP FRICTION NUT COPILOT’S GOVERNOR COLLECTIVE COLLECTIVE INCREASE/DECREASE STICK FRICTION NUT...
Page 107 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-2. ENGINE PRE-START COCKPIT CHECK ELECTRICAL POWER - OFF CHECK All cabin doors CLOSED AND SAFELOCKED ADJUST Anti−torque pedals NOTE : Adjust pedal position to insure that the pedals can be moved throughout the entire range of travel.
Page 108 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures CHECK Magnetic compass heading SELECT card CHECK Static position of all instruments Altimeter All electrical switches Radio switches Circuit breakers OPEN (IN) Fuel shutoff valve Attempting to start the engine with any bleed air devices ON, may CAUTION result in a ‘‘Hot start’’.
Page 109 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures Early Generic Configuration: Place the Reignition Test switch in the GND TEST position (full up). Verify that the ENGINE OUT warning and RE−IGN caution lights illuminate, the audible engine out warnings activate (both external horn in the cabin and internal within the ICS system), and the sound of the ignitor firing is heard.
Page 110 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-3. ENGINE START RECHECK Cyclic stick − trimmed neutral; friction ON Do not attempt engine start with cyclic stick in positions other than CAUTION neutral. Damage to rotor head and controls will result.
Page 111 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures During starts, overtemperatures of 810°C and above for 10 seconds CAUTION or less with a momentary peak at 927°C for not more than 1 second are permitted. Consult Rolls Royce Operation and Maintenance Manual if these limits are exceeded.
Page 112 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures CHECK All other engine instruments engine and rotor rpm indicators for superimposed needles. Malfunctions are indicated if rotor and engine rpm indicator needles CAUTION are not superimposed. Shut down engine if this condition exists.
Page 113 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures FULL OPEN Twistgrip CAUTION Avoid rapid acceleration when parked on slippery surfaces. NOTE : If the engine has been shut down for more than 15 minutes, stabilize at idle for 1 minute before increasing power.
Page 114 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures :ENGINE BLEED AIR SYSTEMS CHECKS CHECK TOT CABIN HEAT (if installed) − ON − Observe 30−40°C INCREASE/ increase in TOT, then OFF. DECREASE CHECK TOT Engine ANTI−ICE ON − Observe increase 10−20°C in TOT, INCREASE/ then OFF.
Page 115 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-5. BEFORE TAKEOFF RECHECK All caution and warning lights out RECHECK Engine oil pressure − 90 to 130 psi CHECK READING Ammeter NOTE : Ammeter reading will fluctuate slightly when anti-collision lights are on.
Page 116 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures AS REQUIRED Engine ANTI−ICE: Use engine ANTI−ICE when OAT is below 5°C (41°F) and visible moisture is present. Check for TOT increase when turning anti−ice ON NOTE : Hover performance is reduced with ANTI-ICE ON (Ref. Section V).
Page 117 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-6. TAKEOFF NOTE : For takeoff in noise-sensitive areas, refer to paragraph 4-18 for noise impact reduction procedures. Determine that hover area and takeoff path are clear. Follow normal helicopter takeoff procedure with N set at 98 percent.
Page 118 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-7. CRUISE Cyclic trim: use proper trimming procedures described for climbout. AS DESIRED SCAV AIR (if installed) Above 50 knots and 50−foot altitude above terrain, select N between 99 and 100 percent for best comfort level.
Page 119 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-9. PRACTICE AUTOROTATION Perform throttle rigging check prior to attempting practice WARNING autorotations (paragraph 4-4). Misrigging of the throttle control may result in inadvertent flameout during rapid closing of the twistgrip to the ground idle position.
Page 120 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures Autorotation RPM: Normal rotor RPM (collective fully down) is 485±5 RPM at 2516 pounds gross weight at sea level, 60 knots. Rotor speed will decrease approximately 7 RPM for each 100 pound reduction in gross weight and increase approxi−...
Page 121 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-13. ENGINE/AIRCRAFT SHUTDOWN Care should be taken when rotating the twistgrip to the ground CAUTION idle position and from ground idle to the cutoff position if the helicopter is parked on a icy or slippery surface (helicopter may spin in direction of main rotor blade rotation).
Page 122 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures CHECK Engine out warning at 55 percent N NOTE : Early Generic Configuration: ENG OUT light only - no audio . Late Generic Configuration: ENGINE OUT light and audio horn .
Page 123 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-14. POST FLIGHT CHECK Aircraft−investigate any suspected damage CHECK Fuel and oil leaks REPLENISH IF LOW Engine oil tank for correct oil level NOTE : Oil level should be checked within 15 minutes after shutdown.
Page 124 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-16. YSAS CHECK Turn YSAS switch ON and confirm that the trailing edge of the right vertical stabilator is at its nominal position (approximately 2 inches inboard of the 5 degree mark on the degree plate located on the upper surface of the horizontal stabilizer).
Page 125 CSP-520N-1 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL Normal Procedures 4-18. NOISE IMPACT REDUCTION PROCEDURES Safe operation of the helicopter always has the highest priority. CAUTION Utilize the following procedures only when they will not conflict with safe helicopter operation. Certain flight procedures are recommended to minimize noise impact on sur−...
Page 127 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 E C T I O N ERFORMANCE TABLE OF CONTENTS PARAGRAPH PAGE 5−1. General ............. .
Page 128 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 PARAGRAPH PAGE Figure 5−13. Hover Ceiling VS Gross Weight, Out of Ground Effect, Engine Air Particle Separator Inlet, Takeoff Power ..5−19 5−8. Power Check Chart − Allison 250−C20R/2 .
Page 129 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data SECTION V PERFORMANCE DATA 5–1. GENERAL This section contains baseline helicopter performance information as defined within certain conditions such as airspeed, weight, altitude, temperature, wind velocity and engine power available. Data is applicable to the basic helicopter without any optional equipment installed unless otherwise noted.
Page 130 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–3. AIRSPEED CALIBRATION CURVE Description: The chart shows the difference between indicated and calibrated airspeeds. Indicated airspeed (IAS) corrected for position and instrument error equals calibrated airspeed (CAS). Use of Chart: Use the chart as illustrated by the example.
Page 131 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data INDICATED AIRSPEED (KTS) F05–013 Figure 5–1. Airspeed Calibration Curve FAA Approved Original 5–3...
Page 132 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–4. DENSITY ALTITUDE CHART Description: The chart allows a quick estimation of the density altitude when pressure altitude and OAT are known. This chart should be used for determining density altitude for use with gross weight limits for the HV Diagram and speed for Best Rate of Climb Chart.
Page 133 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 1.36 1.34 1.32 1.30 1.28 1.26 1.24 1.22 1.20 1.18 1.16 1.14 1.12 1.10 1.08 1.06 1.04 1.02 1.00 –2 –40 –30 –20 –10 TEMPERATURE, DEGREES C –40 –30 –20 –10 TEMPERATURE, DEGREES F F05–014...
Page 134 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–5. SPEED FOR BEST RATE OF CLIMB Description: This chart shows the indicated airspeed to use for the best rate of climb at any given density altitude. Use of Chart: Use the chart as illustrated by the example below.
Page 135 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 18000 16000 14000 12000 10000 8000 6000 4000 2000 INDICATED AIRSPEED – KNOTS F05–015A Figure 5–3. Speed for Best Rate Of Climb FAA Approved Original 5–7...
Page 136 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–6. HEIGHT VELOCITY DIAGRAM/GROSS WEIGHT LIMITS FOR HEIGHT VELOCITY DIAGRAM Height Velocity Diagram (Ref. Figure 5−4) Description Airspeed/altitude combinations to be avoided in the event of an engine failure during takeoff are shown in the height−velocity diagram.
Page 137 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç Ç...
Page 138 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 14000 12000 10000 8000 6000 4000 2000 2200 2400 2600 2800 3000 3200 3400 3600 GROSS WEIGHT – POUNDS F05–017 Figure 5–5. Gross Weight Limits For Height Velocity Diagram FAA Approved 5–10...
Page 139 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–7. HOVER CEILING VS GROSS WEIGHT Description: The hover ceiling charts show the maximum hover weight capability in ground effect (IGE) or out of ground effect (OGE) for known conditions of...
Page 140 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 65 LBS WHEN ENGINE EXHAUST STACKS WITHOUT EXTENDED DEFLECTORS ARE INSTALLED.
Page 141 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 65 LBS WHEN ENGINE EXHAUST STACKS WITHOUT EXTENDED DEFLECTORS ARE INSTALLED.
Page 142 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 65 LBS WHEN ENGINE EXHAUST STACKS WITHOUT EXTENDED DEFLECTORS ARE INSTALLED.
Page 143 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 65 LBS WHEN ENGINE EXHAUST STACKS WITHOUT EXTENDED DEFLECTORS ARE INSTALLED.
Page 144 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO PARTICLE SEPARATOR (SCAV AIR OFF) AND ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 1. 110 LBS WITHOUT MIST ELIMINATOR AND SCAV AIR ON 2.
Page 145 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO PARTICLE SEPARATOR (SCAV AIR OFF) AND ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 1. 110 LBS WITHOUT MIST ELIMINATOR AND SCAV AIR ON 2.
Page 146 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO PARTICLE SEPARATOR (SCAV AIR OFF) AND ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 1. 110 LBS WITHOUT MIST ELIMINATOR AND SCAV AIR ON 2.
Page 147 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 20000 THIS CHART BASED ON CABIN HEAT AND ENGINE ANTI–ICE OFF; ELECTRICAL LOAD OF 10 AMPS. APPLICABLE TO PARTICLE SEPARATOR (SCAV AIR OFF) AND ENGINE EXHAUST STACKS WITH EXTENDED DEFLECTORS. REDUCE WEIGHT: 1. 110 LBS WITHOUT MIST ELIMINATOR AND SCAV AIR ON 2.
Page 148 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 5–8. POWER CHECK CHART – ALLISON 250–C20R/2 Description: The Power Check Chart shows the relationship of engine torque, turbine outlet temperature, and horsepower at various conditions of pressure alti tude and OAT for an Allison 250−C20R/2 engine producing specification power as installed in the Model 500N helicopter.
Page 149 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data Example 1: WANTED: Check engine performance DATA OBTAINED DURING FLIGHT: Torque = 91.0 psig = 750°C = 1000 feet = 19°C Specification TOT (from chart): 760°C Compare the specification TOT of 760°C with the TOT observed during flight (750°C for this example).
Page 151 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Performance Data 100 105 F05–026 TURBINE OUTLET TEMPERATURE–°C TORQUE (psi) Figure 5–14. Power Check Chart – Allison 250–C20R/2 FAA Approved Original 5–23/(5–24 blank)
Page 153 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data E C T I O N EIGHT AND ALANCE TABLE OF CONTENTS PARAGRAPH PAGE 6−1. Weight and Balance Characteristics ........
Page 155 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data SECTION VI WEIGHT AND BALANCE DATA 6–1. WEIGHT AND BALANCE CHARACTERISTICS Weight and balance characteristics: Maximum certified gross weight − 3350 pounds. Minimum flying weight − 1796 pounds. Longitudinal Reference Datum 100 inches forward of rotor centerline (rotor hub centerline is located at Station 100).
Page 156 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data 3350 1497 kg 3300 1406 kg 3100 2900 1315 kg 1225 kg 2700 2500 1134 kg 2300 1043 kg 2100 953 kg 1900 862 kg MINIMUM 815 kg 1796...
Page 157 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data ROTOR C L 78.5 100.0 124.0 CARGO COMPARTMENT CG OF COPILOT/ PASSENGER 15.0 168..8 + 15.5 + 12.2 +0.8 REFERENCE DATUM CG OF CENTER PASSENGER –12.2 –13.0 CG OF PILOT 105.0...
Page 158 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data F05–029 Figure 6–2. Reference Coordinates (Sheet 2 of 2) 6–4 Original...
Page 159 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data Aircraft Actual Weight Model 500N Serial No. Registration No. Date 7/11/91 Weighed by J Doe Witnessed by R Doe EMPTY FULL FUEL OIL, ENGINE OIL, MAIN GEARBOX OIL, FAN GEARBOX...
Page 160 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data MODEL 500N SERIAL NO. REGISTRATION NO. DATE 7/11/91 EXAMPLES OF FORWARD, AFT, AND LATERAL LOADING LONG. LONG. EXAMPLE 1, FORWARD WEIGHT MOMENT (LBS.) (IN.) (IN.–LB.) BASIC WEIGHT (WITH SINGLE CONTROLS) 1704.6...
Page 161 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data TABLE 1 URPLUS ISSING QUIPMENT Model 500N Serial No. Registration No. Date 7/11/91 WEIGHT ARM – INCHES MOMENT – IN/LBS EQUIPMENT – ITEM LONG LATR LONG LATR SURPLUS EQUIPMENT TOTAL: ( 10.2 )
Page 162 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data Figure 6–5. Sample Weight and Balance Record 6–8 Original...
Page 163 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data 6–2. WEIGHT AND BALANCE CRITERIA Use the delivered weight as recorded in the Weight and Balance Record in serted in this section to perform all weight and balance computations. Deliv ered weight includes oil and unusable fuel.
Page 164 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data EXAMPLE I. Longitudinal CG Calculation – Passenger Items Weight Moment (lb) (in.–lb) Delivered Weight 1,705 193,721 Pilot 12,495 Passenger − Fwd Outboard 12,495 Passenger − Aft R/H 17,850 Passenger − Aft L/H 17,850 Utility Stowage (Station 52.9)
Page 165 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data 6–5. LONGITUDINAL LOADING OF CARGO The large aft compartment of the Model 520N provides great flexibility in the variety of cargo loads it can accommodate. In general, the placement of cargo CG within 4 inches of the center of the compartment will ensure that the helicopter will be within the approved CG limits.
Page 166 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data EXAMPLE II. Longitudinal CG Calculation – Passenger and Cargo Weight Moment (lb) (in.–lb) Items Delivered Weight 1,705 193,721 Pilot 12,495 Passenger − Fwd Outboard 12,495 Cargo 1000 100,000 1. Zero Fuel Weight...
Page 167 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data 6–6. PERMISSIBLE LATERAL LOADINGS Safe operation of this helicopter requires that it be flown within established lateral as well as longitudinal center of gravity limits. It is therefore imperative that lateral center of gravity control be exercised.
Page 168 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data EXAMPLE III. Lateral CG Calculation – Passenger and Cargo Weight Lateral Lateral Moment Items (lb) Arm (in) (in.–lb) Delivered Weight 1,705 −0.23 −392 Pilot (L/H) −13.0 −2,210 Passenger − Fwd (R/H) +15.5...
Page 169 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data F05–034 Figure 6–6. Fuel Station Diagram (Jet–A at 6.8 Pounds per Gallon) (Sheet 1 of 2) Original 6–15...
Page 170 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data FUEL QUANTITY (GALLONS) F05–035 Figure 6–6. Fuel Station Diagram (Jet–B at 6.5 Pounds per Gallon) (Sheet 2 of 2) 6–16 Original...
Page 171 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data Table 6–2. Weights and Longitudinal Moments – Pilot, Passenger, Baggage Pilot and Passenger Weights and Longitudinal Moments Moment Moment Moment (in.–lb) (in.–lb) (in.–lb) Passenger Weight (lb) Pilot or Fwd...
Page 172 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data Table 6–3. Weights and Lateral Moments – Pilot, Passenger, Baggage Moment Moment Moment Moment (in.–lb) (in.–lb) (in.–lb) (in.–lb) Passenger Weight Pilot Passenger Aft Passenger Passenger (lb) Center Fwd R/H and L/H R/H Fwd ±...
Page 173 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data 6–8. INTERNAL LOADING OF CARGO The following instructions should be followed when carrying internal cargo. Rope, cable, or equivalent must have a minimum loop strength of 1,800 pounds. Restrain the cargo from shifting by using the correct number of restraining loops in accordance with Table 6−4.
Page 174 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Weight and Balance Data VIEW I LOOP FOR VERTICAL AND LATERAL RESTRAINT CARGO FLOOR VIEW SHOWING LOCATION OF CARGO TIEDOWN POINTS AND LOOPS − MINIMUM LOOP STRINGTH − 1800 LB WRAP CONTAINER WITH SIMILAR STRAP SUCH...
Page 175 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Handling Servicing and Maintenance E C T I O N ANDLING, ERVICING AINTENANCE TABLE OF CONTENTS PARAGRAPH PAGE 7−1. Helicopter Components ..........
Page 177 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 SECTION VII HANDLING SERVICING AND MAINTENANCE 7–1. HELICOPTER COMPONENTS The major components of the helicopter are shown in Figure 7−1. 7–2. USE OF EXTERNAL POWER An external receptacle is located at the right side of the pilot’s compartment seat structure.
Page 178 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 SAS CONTROL ACTUATOR STATOR ENGINE ASSY W/EXTENDED DEFLECTORS ENGINE ASSY W/O EXTENDED DEFLECTORS F05–038 Figure 7–1. MD 500N Helicopter – Major Components FAA Approved 7–2 Original...
Page 179 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–4. GROUND HANDLING WHEELS Standard ground handling wheels, available as a special tool for helicopters not equipped with floats, are used for moving helicopter by hand and for towing helicopter (Ref. Figure 7−2).
Page 180 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–5. MOVING AND TOWING HELICOPTER Manual moving: Excessive lead–lag load applied to the main rotor blades during CAUTION ground handling can result in damage to the elastomeric damper buns and failure of the damper assembly. Operators should use extra caution to avoid lead–lag loads in excess of 35 pounds at...
Page 181 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–6. PARKING AND MOORING Parking (Ref. Figure 7−3): To prevent rotor damage from blade flapping (droop stop pound- CAUTION ing) as a result of air turbulence from other aircraft landing, taking off or taxiing or sudden wind gusts, rotor blades should be secured whenever helicopter is parked.
Page 182 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 BLADE SOCK (5 PLACES) TIEDOWN TETHER CABLE OR MANILA ROPE MOORING ANCHOR (4 PLACES) ENGINE EXHAUST COVER ZIPPER AIR INLET FAIRING COVER PITOT TUBE COVER PITOT TUBE TIE CORD COVER INSTALLATION DOOR ACCESS...
Page 183 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–7. SERVICING – GENERAL Servicing helicopter includes replenishment of fuel, changing or replenishment of oil and other such maintenance functions. Fuels, oils, other servicing materials and capacities are listed in Table 7−1. Locations of servicing points are shown in Figure 7−4.
Page 184 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Specification Material Manufacturer MIL−PRF−23699 Series Mobil Jet Oil II ExxonMobil Lubricants Turbonycoil NYCO S.A. 600) 66, Champs−Elysees−51 Rue De Ponthieu F−75008 Paris, France Aeroshell/Royco Turbine Royal Lubricants Company, Oil 500 Inc. River Road, P.O. Box 518...
Page 185 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Specification Material Manufacturer 5. Fuel Cells − Standard Nonself−sealing, Capacity: 64.0 US Gal (242 liters), 416 pounds Optional Self−sealing, Capacity: 62.0 US Gal (234 liters), 402 pounds. Refer to Rolls−Royce 250 Series Operations Manual for complete fuel specifications.
Page 186 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Specification Material Manufacturer One−Way Lock Continued Specification Material Manufacturer MIL–PRF–6083 Brayco Micronic 783 Castrol Industrial North America Inc. Royal Lubricants Company, Royco 783 Inc. Hydraunycoil FH−6 NYCO, S.A. 9. Battery (NiCad) − Capacity: As required...
Page 187 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 OIL FILTER BYPASS INDICATOR (369F5100 M/R TRANSMISSION ONLY) FILLER SIGHT GAGE AFT AND MAIN TRANSMISSION OIL LEVEL SIGHT GAUGES & AFT TRANSMISSION BATTERY MAIN TRANSMISSION FILLER LIQUID LEVEL SIGHT GAGE EXTERNAL POWER RECEPTCLE...
Page 188 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 ENGINE WASH ENGINE OIL FITTING TANK DRAIN MAIN TRANSMISSION OIL COOLER DRAIN ENGINE OIL COOLER DRAIN SCAVENGE OIL FILTER STATION 137.50 BULKHEAD OIL FILTER BYPASS INDICATOR 250−C20/R2 SP ENGINE BYPASS INDICATOR ENGINE FUEL FILTER F05–043–2...
Page 189 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–8. FUEL SYSTEM – SERVICING Refueling vehicle should be parked a minimum of 20 feet from helicopter dur ing fueling operation. Before starting fueling operation, always ground fueling nozzle or fuel truck to GROUND HERE receptacle (Ref.
Page 190 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Fuel draining: Fuel draining should be accomplished with helicopter as level as possible. The fuel system may be defueled in two ways: One is to defuel through the filler port, using a pump. The other method is to open the drain valve on fuselage underside.
Page 191 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Aft transmission: A liquid level sight gauge for checking oil level is located on the lower right hand side of the transmission housing (Ref. Figure 7−4). Check oil level by viewing sight gauge.
Page 192 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–13. CLEANING AIRCRAFT EXTERIOR AND ROTOR BLADES Use care to prevent scratching of aluminium skin when cleaning CAUTION main rotor blades. Never use volatile solvents or abrasive materials. Never apply bending loads to blades or blade tabs during cleaning.
Page 193 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 NOTE : On transmission input gear oil seals with less that 2 hours of operation, some seepage or wetting of adjacent surfaces is normal until seal is wetted and worn–in (seated). If seepage continues at rate of one drop per minute or less, seal may be continued in service.
Page 194 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Start engine (Ref. Section IV). After idle stabilizes, accelerate engine to 100 percent N . Operate until oil temperature shows an increase and ammeter reads zero. Shut down engine (Ref. Section IV). Replenish fuel as necessary.
Page 195 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 DOOR FRAME PILOT’S DOOR PASSENGER/CARGO COMPARTMENT DOOR (LH SHOWN, RH SIMILAR) FUSELAGE STRUCTURE HINGE PIN DOOR HINGE DOOR STRUCTURE F60–043 Figure 7–5. Pilot and Passenger/Cargo Door Removal FAA Approved Revision 2 7–19...
Page 196 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 7–19. SPECIAL OPERATIONAL CHECKS AND PROCEDURES Cleaning engine compressor: Water wash provisions are incorporated in current configuration helicopters (Ref. Figure 7−4). Engine compressor cleaning should be performed by qualified personnel in accordance with the HMI and the Engine Operation and Maintenance Manual.
Page 197 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Procedures: Ensure engine anti−ice, cabin heat, and scav air (if installed) are off prior to engine wash or rinse. Water injection will be started three seconds prior to starter engagement. Motor the engine with the twistgrip in CUTOFF.
Page 199 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Additional Operations and Performance Data VIII E C T I O N DDITIONAL PERATIONS ERFORMANCE TABLE OF CONTENTS PARAGRAPH PAGE 8−1. ICAO Noise Characteristics ..........
Page 201 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Additional Operations and Performance Data SECTION VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA 8–1. ICAO NOISE CHARACTERISTICS International Civil Aviation Organization (ICAO) Noise Levels. The following noise levels comply with ICAO Annex 16 noise requirements and were obtained by using approved analysis techniques and approved data from actual noise tests.
Page 203 ......... . . 9−1 Table 9−1. Optional Equipment MD 520N Helicopter .....
Page 205 OPTIONAL EQUIPMENT 9–1. GENERAL INFORMATION This section provides general supplemental information on optional equipment for the MD 520N Model 500N Helicopter. The information includes a listing of usable optional equipment and compatibility of combined equipment on the he licopter. NOTE...
Page 206 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Table 9–1. Optional Equipment MD 520N Helicopter Equipment Part No. Publication No. * Extended landing gear 369D290007 CSP−520N−1 * Rotor brake 369H90123 CSP−520N−1 * Engine air particle separa 500N90148 CSP−520N−1 tor filter...
Page 207 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit 9–5. OPERATING INSTRUCTIONS: CARGO HOOK KIT PART I GENERAL The MDHI 369H90072−523 Cargo Hook Kit consists of a cargo hook which at taches to the fuselage keel beam, electrical connections to provide the pilot with cargo release or jettison capability using a switch on the cyclic stick, and a manual backup release mechanism.
Page 208 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit PART II LIMITATIONS Weight Limitations: Maximum takeoff and landing gross weight 3350 pounds. Weight CAUTION in excess of 3350 pounds must be external and jettisonable. Maximum Rotorcraft − Load Combinations operating gross weight 3850 pounds (FAR 133).
Page 209 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit Cargo Hook Limitations: Cargo hook structural load limit is 2000 pounds. Airspeed Limitations: With no load on hook, airspeed limits are unchanged. With load on hook, airspeed limits are presented on the exterior load V placards.
Page 210 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit Placards: Make placards stating approved load class(es) and occupancy limitations. Display placards in a conspicuous location in cockpit. Placard stating, ‘‘External Load Limit 2000 Pounds’’ installed on or next to cargo hook.
Page 211 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit PART III EMERGENCY AND MALFUNCTION PROCEDURES ENGINE FAILURE: The presence of an external load may further complicate a failed engine condition. Release of loads attached through the cargo hook should be ac complished as soon as practical;...
Page 212 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit PART IV NORMAL PROCEDURES Normal Operation: Preflight Place battery switch in BAT position and check that HOOK circuit breaker is IN. Push cargo load ring (D−ring or suitable substitute) into hook throat.
Page 213 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit EXTERNAL RELEASE (TURN CLOCKWISE) ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK (LOAD BEAM) Figure 9–4. Cargo Hook PART V PERFORMANCE DATA Refer to Section V for IGE and OGE hover performance to assist in planning operations with the cargo hook.
Page 214 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Cargo Hook Kit PART VI WEIGHT AND BALANCE DATA The following table of Cargo Hook Loading Data should be used by the opera tor to assist in evaluating the helicopter center of gravity for various hook load weights.
Page 215 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Anti–Ice Airframe Fuel FIlter 9–6. OPERATING INSTRUCTIONS: ANTI–ICE AIRFRAME FUEL FILTER PART I GENERAL The MDHI Anti−Ice Airframe Fuel Filter is designed to strip the fuel of ice particles prior to entering the engine fuel system. Installation of the filter will delete the requirement for use of fuel containing anti−ice additives.
Page 216 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Anti–Ice Airframe Fuel FIlter PART II LIMITATIONS No change. PART III EMERGENCY AND MALFUNCTION PROCEDURES ANTI−ICE AIRFRAME FUEL FILTER Indications: Yellow caution indicator ON. FRAME FILTER Conditions: Anti−ice airframe fuel filter becoming clogged with ice or other solid contaminants.
Page 217 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Anti–Ice Airframe Fuel FIlter PART IV NORMAL PROCEDURES Preflight checks: NOTE : The following checks should be performed as part of the engine compartment checks listed in the basic preflight checklist in Section IV.
Page 218 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Anti–Ice Airframe Fuel FIlter TEST BUTTON FIREWALL FILTER BOWL ANTI−ICE DRAIN VALVE Figure 9–5. Anti–Ice Airframe Fuel Filter FAA Approved 9–14 Original...
Page 219 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats 9–7. OPERATING INSTRUCTIONS – EMERGENCY FLOATS PART I GENERAL The MDHI Emergency Float Kit, consists of inflatable bag−type floats intended for use in emergency landings only, during over−water operation. It is fur nished with squib−actuated valves and with steel pressure vessels.
Page 220 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats PART II LIMITATIONS Night flight over water beyond autorotational capability to ground is prohib ited, unless 369D292032 Night Landing Kit is installed. Flight with floats inflated, or at time of inflation, is limited to the conditions of altitude and temperature presented on the EMERGENCY FLOATS INFLATED PLACARD.
Page 221 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats Gross weight limitations: Minimum gross weight is 1949 pounds. Center of gravity limits: Longitudinal C.G. Limit Lateral C.G. Limit Gross Weight (lb) (Sta−in.) (Sta−in.) Forward Aft* (−) Left, (+) Right ±...
Page 222 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats EMER FLOATS–INFLATED IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 1949 TO 3350 LBS ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 22 KTS (85K MIN);...
Page 223 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats Inflation should be accomplished at 2,000 feet or less above landing sur face to minimize differential pressure change with altitude change. For over−water operation in conditions near the Height−Velocity Diagram, immediate pilot reaction will be required to ensure float inflation prior to water contact.
Page 224 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats PART IV NORMAL PROCEDURES Preflight checks: Check condition and security of stowed float package. Check pressure gauge in each float package. If the pressure vessel is at 70°F (21.1°C), the pressure should read within 3000 to 3500 psig (Ref.
Page 225 MD 520N (500N) ROTORCRAFT FLIGHT MANUAL CSP–520N–1 Optional Equipment Emergency Floats PRESSURE GAGE INSPECTION WINDOW RIGHT HAND SKID (LEFT HAND SIMILAR) PRESSURE GAGE F02–030 Figure 9–7. Float Pressure Gauge PART V PERFORMANCE DATA Hover Performance with Stowed Floats No change from that of the basic helicopter with extended landing gear.

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