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MD Helicopters 369 Series Flight Manual

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Manual:
CSP–D–1
Model:
369D
Reissue #1: 18 August 1998
Revision 5
3 September 2004
The attached manual is a reprint of the MD 500D flight manual and includes all revisions
thru Revision 5. Refer to page F−vii for information regarding changed data.
FILING INSTRUCTIONS:
R
Remove all pages in Sections I thru IX including front matter (do not re-
move aircraft weight and balance data or STC supplements), and re-
place them with the new flight manual.
Operators with questions regarding this reprint may contact:
Mike Zale at 480.346.6558 from 6:00 AM to 2:30 PM MST or e–mail
mike.zale@mdhelicopters.com.
369 Series
RFM Revision
A/(B blank)

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Summary of Contents for MD Helicopters 369 Series

  • Page 1 369 Series RFM Revision Manual: CSP–D–1 Model: 369D Reissue #1: 18 August 1998 Revision 5 3 September 2004 The attached manual is a reprint of the MD 500D flight manual and includes all revisions thru Revision 5. Refer to page F−vii for information regarding changed data.
  • Page 3 MD 500D 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: _________________ F02–001 F–0...
  • Page 5 THE ‘‘AIRWORTHINESS LIMITATIONS’’ LISTED IN SECTION 04−00−00 OF CSP−HMI−2 SHALL BE COMPLIED WITH. THIS MANUAL MUST BE KEPT IN THE HELICOPTER AT ALL TIMES. Copyright E 1999−2004 by MD Helicopters, Inc. All rights reserved under the copyright laws. Revision 4...
  • Page 6 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LOG OF REVISIONS BY DATE FAA / NON–FAA REVISIONS REVISION NUMBER/DATE Original Issue 6 December 1976 Revision 1 ..20 January 1977 Revision 2 ..29 April 1977 Revision 3 .
  • Page 7 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) TABLE OF CONTENTS PARAGRAPH PAGE Cover ..............Title Page .
  • Page 8 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) PARAGRAPH PAGE 2−11. Fuel System Limitations ..........2−10 2−12.
  • Page 9 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) PARAGRAPH PAGE 4−12. Running Landing ........... . . 4−24 4−13.
  • Page 10 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) PARAGRAPH PAGE 7−8. Fuel System − Servicing ..........7−13 7−9.
  • Page 11 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) SUMMARY OF REVISIONS TO THE ROTORCRAFT FLIGHT MANUAL NOTE: Revisions are listed below by number with appropriate remarks. REVISION REMARKS NUMBER Revision 5 Section I: Removed company logo from all pages and replaced refer ences to McDonnell Douglas with MDHI.
  • Page 12 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER FRONT Cover − − − − − − − − Revision 3 MATTER F−i Revision 4 −...
  • Page 13 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 1−13 − − − − − − − − Revision 5 1−14 − − − − − − − − Revision 5 1−15 −...
  • Page 14 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 3−1 Revision 5 − − − − − − − − 3−2 Revision 5 − − − − − − − − 3−3 Revision 5 −...
  • Page 15 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 4−5 Revision 4 − − − − − − − − 4−6 Revision 4 − − − − − − − − 4−7 Revision 4 −...
  • Page 16 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 5−7 Revision 5 − − − − − − − − 5−8 Revision 5 − − − − − − − − 5−9 Revision 5 −...
  • Page 17 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 6−10 − − − − − − − − Revision 5 6−11 − − − − − − − − Revision 5 6−12 −...
  • Page 18 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 7−20 − − − − − − − − Revision 5 7−21/(7−22 blank) − − − − − − − − Revision 5 VIII 8−i/(8−ii blank)
  • Page 19 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 9−25 Revision 5 − − − − − − − − 9−26 Revision 5 − − − − − − − − 9−27 Revision 5 −...
  • Page 20 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) LIST OF EFFECTIVE PAGES FAA APPROVED NON FAA APPROVED SECTION PAGE NUMBER REVISION NUMBER REVISION NUMBER 9−61 Revision 5 − − − − − − − − 9−62 Revision 5 − − − − − − − − 9−63 Revision 5 −...
  • Page 21 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General E C T I O N ENERAL TABLE OF CONTENTS PARAGRAPH PAGE 1−1. Introduction ............1−1 1−2.
  • Page 23 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General SECTION I GENERAL 1–1. INTRODUCTION The Rotorcraft Flight Manual has been prepared to provide the pilot with all information necessary to accomplish the intended mission with the maximum amount of efficiency and safety. 1–2.
  • Page 24 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 and tail rotor. Use of seat belts and shoulder harnesses.
  • Page 25 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General SECTION IV − NORMAL PROCEDURES (FAA Approved) Normal operating procedures from preflight through shutdown. The data is recommended by MDHI. SECTION V − PERFORMANCE DATA (FAA Approved) Aircraft performance as defined within certain conditions, such as airspeed, weight, altitude, temperature, humidity, and wind velocity.
  • Page 26 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General 1–9. ABBREVIATIONS Federal Aviation Administration Air Conditioner Federal Aviation Above Ground Level Regulation Alternate; Altitude Fuselage Station Auxiliary Power Unit Foot, Feet Attitude AUTO Automatic Gallons Auxiliary Generator Control Unit Generator Ground Power Unit Battery Gross Weight...
  • Page 28 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General Pounds per Square Inch Power Kilogram KCAS Knots Calibrated Airspeed Quantity Kilogram(s) KIAS Knots Indicated Airspeed Right Kilometer Revolutions per Minute Kilometers per Hour Rotor KTAS Knots True Airspeed Seconds Left; Liters Sound Exposure Level LAT.
  • Page 29 Illustrated Parts Catalog (IPC) Service Information Notices and Letters New and revised publications are available through MDHS Subscription Ser vice. Further information may be obtained by contacting: MD Helicopters, Inc. M615−G048 4555 E McDowell Rd Mesa, AZ 85215−9734 Revision 5...
  • Page 30 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General or your local Service Center, Distributor, or Sales Company. All persons who fly or maintain MDHI helicopters are urged to keep abreast of the latest information by using the subscription service. 1–11.
  • Page 31 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General The tailboom is a monocoque structure of aluminum alloy frames and skin. The tailboom is the supporting attachment structure for the stabilizers, tail rotor transmission and tail rotor. The tailboom also houses the tail rotor transmission drive shaft;...
  • Page 32 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General ing autorotation and engine shutdown. The main drive shaft connects to the main rotor transmission input shaft. The engine oil cooler blower is belt driven off the main drive shaft. The oil cooler blower draws cooling air from the air inlet fairing to supply ambient air to the engine and transmission oil coolers and to the engine compartment.
  • Page 33 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General 1–12. 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 ARMED) on the instrument panel, a RE−...
  • Page 34 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General 1–13. 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 35 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General NOTES: 1. HELICOPTER ON GROUND. (MAXIMUM COMPRESSED DIMENSION 6.8). 2. IF OPTIONAL EXTENDED LANDING GEAR IS INSTALLED, ADD 0.63 TO ALL VERTICAL DIMENSIONS. 3. ALL DIMENSIONS IN FEET F02−001 Figure 1–1. MD 500D Principal Dimensions – Standard Landing Gear Revision 5 1–13...
  • Page 36 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) General 1–14. 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 37 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 ALTERNATE METHOD: °...
  • Page 38 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 45.425...
  • Page 39 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 4.267...
  • Page 40 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 Figure 1–4.
  • Page 41 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) General EXAMPLE 1: 29.44 IN. HG = 997 MBAR EXAM PLE 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 42 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 PRESSURE PRESSURE...
  • Page 43 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) E C T I O N IMITATIONS TABLE OF CONTENTS PARAGRAPH PAGE 2−1. Flight Restrictions ........... . 2−1 2−2.
  • Page 45 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) SECTION II LIMITATIONS NOTE : Unless otherwise stated, the restrictions and limitations put forth in this section apply to MD 500D (Model 369D) Helicopters equipped with either the Allison 250–C20B or 250–C20R/2 engines 2–1.
  • Page 46 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) Flight with doors removed is approved under the following conditions. Approved doors−off configurations All doors off. Both rear doors off. Any one door off. Maximum V is 130 knots IAS for gross weights of 2501 pounds or more and 120 knots IAS for 2500 pounds or less.
  • Page 47 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) 2–2. ENVIRONMENTAL OPERATING CONDITIONS Kinds of operations: This rotorcraft is certified in the normal helicopter category for day and night VFR operation when the appropriate instruments and equipment re quired by the airworthiness and/or operating rules are approved, installed and are in operable condition.
  • Page 48 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 2–4. WEIGHT LIMITATIONS Maximum gross weight: 3000 lbs. Minimum flying gross weight: 1538 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. CG Limits: Ensure helicopter CG and weight are within approved limits throughout flight (Ref.
  • Page 49 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) 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 205 RPM.
  • Page 50 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 2–7. POWERPLANT LIMITATIONS ALLISON 250–C20B Engine torque limits: Maximum takeoff (5 minute): 87.2 psi torque. Maximum continuous: 81.3 psi torque with TOT at or below 738°C. 74.3 psi torque with TOT greater than 738°C. Transient torque limits: 87.3 to 93.0 psi torque for 15 seconds at 103 percent N 93.1 to 97.6 psi torque for 3 seconds at 103 percent N...
  • Page 51 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) Power Turbine (N ) speed limits: É É É É É É É É É É É É É É É É É É É É É É É É É É É É É É É...
  • Page 52 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 2–8. POWERPLANT LIMITATIONS ALLISON 250–C20R/2 Engine torque limits: Maximum takeoff power (5 minute): 87.2 psi torque Maximum continuous: 81.3 psi torque Transient torque limits: 87.3 to 93.0 psi torque for 15 seconds at 103 percent N 93.1 to 97.6 psi torque for 3 seconds at 103 percent N Turbine Outlet Temperature limits: Maximum takeoff (5 minute): 810°C...
  • Page 53 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) Power Turbine (N ) speed limits: É É É É É É É É É É É É É É É É É É É É É É É É É É É É É É É...
  • Page 54 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 2–9. ELECTRICAL SYSTEM LIMITATIONS Generator limits: Maximum continuous: 85 amps 85 to 150 amps: 10 minutes >150 amps: 2 minute limit prior to takeoff during battery recharging cycle only. Battery limits: Flight following a battery overtemperature of 160°F (71°C) or above is pro hibited until the battery has been inspected.
  • Page 55 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) Table 2–1. Unusable Fuel: Standard Non Self–Sealing Fuel Tanks Imp. U.S. Pounds/ Fuel Type Liters Kilograms Jet−A 13.1/5.9 Jet−B 12.5/5.7 Table 2–2. Unusable Fuel: Optional Self–Sealing Fuel Tanks Imp. U.S. Pounds/ Kilograms Fuel Type Liters...
  • Page 56 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) FUEL TEMPERATURE ~ DEG C 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 É É É É...
  • Page 57 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) 2–12. INSTRUMENTATION YELLOW GREEN RED INDICATES MAXIMUM AND YELLOW INDICATES GREEN INDICATES MINIMUM OPERATING LIMITS; CAUTIONARY OPERATING NORMAL OPERATING THE EDGE OF A RED LINE IS THE RANGE. RANGE LIMITING VALUE; THE POINTER BLUE SHOULD NOT ENTER THE RED BLUE INDICATES SPECIAL...
  • Page 58 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) DUAL TACHOMETER (FACE SHOWN TWICE FOR CLARITY) ROTOR RPM 102 AND 103% 410 AND 523 RPM 102 TO 103% 410 TO 523 RPM 113% 6 5 4 PERCENT PRESS AIRSPEED ENGINE OIL PRESSURE (LATER CONFIGURATION) TACHOMETER 59 AND 105...
  • Page 59 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) TURBINE TORQUEMETER OUTLET TEMPERATURE 87.2 PSI 810°C 81.3 TO 87.2 PSI 755 TO 810°C 0 TO 81.3 PSI 360 TO 755°C 74.3 PSI 843°C 738°C ALLISON 250−C20B F02−005−3 TURBINE OUTLET TEMPERATURE TORQUEMETER ANALOG / DIGITAL ANALOG...
  • Page 60 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 2–13. PLACARDS AND DECALS IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2000 OR LESS ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 25K (85K MIN); DO NOT EXCEED CHART V IAS (KNOTS) PRESS ALT X 1000...
  • Page 61 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2501 TO 3000 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 25K (95K MIN); DO NOT EXCEED CHART V Figure 2–6.
  • Page 62 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Limitations (Model 369D) 250–C20R/ 2 IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2001 TO 2500 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 22K (90K MIN); DO NOT EXCEED CHART V 250–C20R/ 2 IAS (KNOTS) PRESS ALT X 1000...
  • Page 63 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Limitations (Model 369D) 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. CAUTION CYCLIC FORCES TO BE TRIMMED TO NEUTRAL DURING...
  • Page 65 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) I I I E C T I O N MERGENCY AND ALFUNCTION ROCEDURES TABLE OF CONTENTS PARAGRAPH PAGE 3−1. General ............. . 3−1 3−2.
  • Page 66 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) PARAGRAPH PAGE 3−13. Fuel System Malfunctions ..........3−22 Fuel Filter .
  • Page 67 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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. Drop in rotor speed.
  • Page 70 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures NOTE : The minimum rate of descent with power off will be attained at 60 KIAS and 410 The maximum glide distance with power off will be attained at 80 KIAS and 410 Glide distances attained during an actual engine out autorotation may be less than the glide distances achieved during practice autorotations when operating at reduced RPM (N...
  • Page 71 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 468.
  • Page 74 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures When aircraft begins to roll, lower collective to full down to minimize blades skipping off the water. Release safety harness and clear the aircraft as soon as the rotor blades have stopped turning Do not inflate personal flotation gear before exiting aircraft.
  • Page 75 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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.
  • Page 76 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures Conditions: Engine compartment fire Procedures: Twistgrip CUTOFF Fuel shutoff valve PULL TO CLOSE BATTERY/EXT PWR switch Passengers/crew EVACUATE IF TIME AND SITUATION PERMIT: Rotor brake (if installed) APPLY Secure area HAVE PASSENGERS AND SPECTATORS MOVE A SAFE DISTANCE FROM THE AIR-...
  • Page 78 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 BATTERY/EXT PWR switch Passengers/crew EVACUATE IF UNABLE TO LAND IMMEDIATELY AND FIRE SOURCE...
  • Page 80 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 (410−523) and at tempt level flight at 60 knots IAS.
  • Page 82 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures 3–10. MAIN ROTOR AND TAIL ROTOR 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 XMSN Indications: Red...
  • Page 84 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures 3–11. FLIGHT CONTROL MALFUNCTIONS ANTI−TORQUE FAILURE Different types of failure may require slightly different techniques for optimum success in recovery. Therefore, it is not possible to provide a standardized solu tion for an anti−torque emergency.
  • Page 85 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures Conditions: Anti−torque failure, fixed tail rotor pitch setting. Procedures: Adjust power to maintain 50 to 60 knots airspeed. Perform a shallow approach and running landing to a suitable area, touching down into wind at a speed between effective translational lift and 30 knots.
  • Page 86 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 87 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 88 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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. Procedures: LAND AS SOON AS POSSIBLE.
  • Page 89 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 90 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures 3–14. ELECTRICAL SYSTEM MALFUNCTIONS BATTERY OVERTEMPERATURE Indications: Red indicator ON. 160F Conditions: Battery overtemperature at 160°F (71°C) or above. Procedures: Battery switch: OFF. Land as soon as possible NOTE : No further flights are authorized until battery is inspected and cause of overtemp corrected.
  • Page 91 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures GENERATOR MALFUNCTION Indications: Yellow indicator ON, and ammeter indicating zero. Conditions: Generator is not powering electrical bus. Procedures: Check generator (GEN) circuit breaker IN. Turn the generator switch OFF, then ON to reset. If GEN OUT indicator remains ON or comes back ON, pull generator cir cuit breaker OUT and insure generator switch is in the ON position for the remainder of the flight.
  • Page 92 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Emergency and Malfunction Procedures 3–15. OTHER MALFUNCTIONS ENGINE AIR PARTICLE SEPARATOR FILTER CLOGGED (IF INSTALLED) Indications: Yellow indicator ON. FILTER CLOGGED NOTE : Certain flight conditions may cause the yellow caution indicator to flicker momentarily.
  • Page 93 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 Figure 3–2.
  • Page 95 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) E C T I O N ORMAL ROCEDURES TABLE OF CONTENTS PARAGRAPH PAGE 4−1. Preflight Requirements ..........4−1 Figure 4−1.
  • Page 97 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures SECTION IV NORMAL PROCEDURES 4–1. PREFLIGHT REQUIREMENTS NOTE : The checks described in this Section apply to the standard configuration MD 500D 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–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) F02−007 Figure 4–1. Pilot’s Preflight Guide FAA Approved 4–2 Revision 4...
  • Page 99 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures DAILY PREFLIGHT CHECKS PRELIMINARY CHECKS Fuel cell drain valve − take sample (Start pump OFF) CHECK FOR CONTAMINANTS Anti−ice fuel filter drain valve (if installed) take sample CHECK FOR (Start pump ON) CONTAMINANTS Do not open fuel filter drain valve unless start pump is ON.
  • Page 100 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) FUSELAGE – RH SIDE Skid, strut fairings, strut cuffs CHECK Position light, skid tip CHECK Fuel tank vent NO OBSTRUCTIONS Fuselage skin CHECK Passenger steps for condition and security CHECK Passenger and cargo doors condition and latching CHECK M/R transmission oil level...
  • Page 101 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures TAILBOOM/TAIL ROTOR Tailboom CHECK: NO DAMAGE ALLOWED Position and anti collision lights CHECK Stabilizers (vertical, horizontal and end plates) CHECK: NO DAMAGE ALLOWED Tail skid CHECK Tail rotor gearbox attachment to tailboom for security and CHECK condition Chip detector and wiring...
  • Page 102 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) Tail rotor drive shaft coupling CHECK: NO DAMAGE ALLOWED Rock tail rotor back and forth in plane of rotation and check main rotor blades for coincidental movement. NOTE : If tail rotor blade tip can move in excess of 3/4 inch (1.9 cm) without coincidental movement of the main rotor blades, inspect tail rotor drive shaft couplings in accordance with the Handbook of Maintenance Instructions.
  • Page 103 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures FUSELAGE – UNDERSIDE Fuselage skin CHECK Fuel tank and other vents NO OBSTRUCTIONS Cargo Hook (if installed) CHECK Antennas CHECK INTERIOR AFT COMPARTMENT Impeller belt CHECK Fuel cell access doors SECURED Controls access door SECURED...
  • Page 104 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) PREFLIGHT CHECKS Perform these checks prior to subsequent flights of the same day. Fluid levels CHECK Engine compartment − fluid leaks and CHECK bypass indicators Air inlet screens/particle separator CHECK Fuel cap, access doors and panels CHECK Main rotor blades...
  • Page 105 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures CLOCK CAUTION AND WARNING LIGHTS ALTIMETER AIRSPEED INDICATOR SCAVENGE AIR (IF INSTALLED) ANTI−ICE SWITCH (250−C20R/2) DUAL TACHOMETER INDICATOR TORQUE GAGE TURBINE OUTLET TEMPERATURE (TOT) INDICATOR TACHOMETER INSTRUMENT CLUSTER FUEL SHUTOFF FRESH AIR VENT VALVE CONTROL...
  • Page 106 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) ENGINE OUT AUDIBLE WARNING HORN CAUTION AND WARNING LIGHTS HOOD LIGHT 2 3 4 5 6 9 10 11 (5 PLACES) 1. BATTERY TEMP 2. START PUMP ON 3. GEN OUT 4.
  • Page 107 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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 (OPTIONAL) SWITCH PILOT’S...
  • Page 108 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) 4–2. ENGINE PRE–START COCKPIT CHECK ELECTRICAL POWER – OFF All cabin doors CLOSED AND SAFELOCKED CHECK Tail rotor pedals ADJUST NOTE : Adjust pedal position to insure that the pedals can be moved throughout the entire range of travel.
  • Page 109 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures Altimeter All electrical switches Radio switches Circuit breakers Fuel shutoff valve OPEN (IN) Attempting to start the engine with any bleed air devices ON, may CAUTION result in a ‘‘Hot start’’. ELECTRICAL POWER –...
  • Page 110 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) Press−to−test caution and warning lights CHECK Caution light dim switch CHECK NOTE : Caution lights will return to bright when all power is removed (BATTERY and GEN OFF) and restored, or by pulling and resetting the PNL LT circuit breaker. Press−to−test AIR FILTER CLOGGED (if installed) and CHECK BATTERY warning and caution lights.
  • Page 111 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures 4–3. ENGINE START Cyclic stick − trimmed neutral; friction ON RECHECK Do not attempt engine start with cyclic stick in positions other than CAUTION neutral. Damage to rotor head and controls will result. Collective stick −...
  • Page 112 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) During starts, overtemperatures above 810°C for 10 seconds or CAUTION less with a momentary peak at 927°C for not more than 1 second are permitted. Consult Allison Operation and Maintenance Manual if these limits are exceeded.
  • Page 113 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures All other engine instruments CHECK engine and rotor rpm indicators for superimposed needles. Malfunctions are indicated if rotor and engine rpm indicator CAUTION needles are not superimposed. Shut down engine if this condition exists.
  • Page 114 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) Twistgrip FULL OPEN Check for unusual aircraft vibration or noise while accelerating CAUTION from ground idle to flight idle. If any unusual vibration or noise oc- curs, this may be an indication of a loose or defective tailrotor dirve- shaft damper.
  • Page 115 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures :ENGINE BLEED AIR SYSTEMS CHECKS CABIN HEAT (if installed) − ON − Observe 30−40°C CHECK TOT increase in TOT, then OFF. INCREASE/ DECREASE Engine ANTI−ICE ON − Observe increase 10−20°C in TOT, CHECK TOT then OFF.
  • Page 116 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) 4–5. BEFORE TAKEOFF All caution and warning lights out RECHECK Engine oil pressure − 90 to 130 psi RECHECK Ammeter CHECK READING NOTE : Ammeter reading will fluctuate slightly when anti–collision lights are on. All cabin doors closed and safelocked RECHECK Cabin heat...
  • Page 117 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures 4–6. TAKEOFF NOTE : For takeoff in noise–sensitive areas, refer to paragraph 4–17 for noise impact reduction procedures. Determine that hover area and takeoff path are clear. Follow normal helicopter takeoff procedure with N set at 103 percent.
  • Page 118 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) 4–7. CRUISE Cyclic trim: use proper trimming procedures described for climbout. SCAV AIR (if installed) AS DESIRED Above 50 knots and 50−foot altitude above terrain, select N between 102 and 103 percent for best comfort level. Use engine anti−icing when OAT is below 5°C (41°F) and visible moisture conditions prevail.
  • Page 119 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) 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–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) Autorotation RPM: Normal rotor RPM (collective fully down) is 485±5 RPM at 2250 pounds gross weight at sea level, 60 knots. Rotor speed will decrease approximately 10 RPM for each 100 pound reduction in gross weight and increase approxi mately 6.5 RPM for each 1000 foot increase in density altitude.
  • Page 121 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures 4–13. ENGINE/AIRCRAFT SHUTDOWN Care should be taken when rotating the twistgrip to the ground idle CAUTION position and from ground idle to the cutoff position if the helicopter is parked on a icy or slippery surface (helicopter may spin in direc- tion of main rotor blade rotation).
  • Page 122 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) NOTE : If thumping or a rapping sound is heard from the drive train during the final revolution of the main rotor, inspect the tail rotor drive shaft couplings in accordance with the HMI.
  • Page 123 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Normal Procedures 4–14. POST FLIGHT Aircraft−investigate any suspected damage CHECK Fuel and oil leaks CHECK Engine oil tank for correct oil level REPLENISH IF LOW NOTE : Oil level should be checked within 15 minutes after shutdown. Logbook entries COMPLETE Flight manual and equipment...
  • Page 124 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL Normal Procedures (Model 369D) 4–16. NORMAL ENGINE RESTART Do not exceed 150°C residual TOT when ignition is attempted. Reduce TOT by motoring engine with starter. Speeds in excess of 15 percent may be experienced. 4–17.
  • Page 125 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Performance Data E C T I O N ERFORMANCE TABLE OF CONTENTS PARAGRAPH PAGE 5−1. General ............. . 5−1 5−2.
  • Page 126 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) PARAGRAPH PAGE Figure 5−12. Hover Ceiling VS Gross Weight IGE, 6 Foot Skid Clearance, Standard Landing Gear, 2−Bladed Tail Rotor, Allison 250−C20R/2 ........5−17 Figure 5−13.
  • Page 127 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) 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 128 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 5–2. DENSITY ALTITUDE 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 129 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) 20000 1.36 1.34 18000 1.32 1.30 16000 1.28 1.26 14000 1.24 1.22 12000 1.20 1.18 10000 1.16 1.14 8000 1.12 1.10 6000 1.08 4000 1.06 1.04 2000 1.02 1.00 0.98 −2000 −40 −30...
  • Page 130 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 5–3. AIRSPEED CALIBRATION 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: To determine calibrated airspeed, the pilot must know the indicated air speed.
  • Page 131 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) INDICATED AIRSPEED – KNOTS F02–011 Figure 5–2. Airspeed Calibration Curve FAA Approved Revision 5 5–5...
  • Page 132 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 5–4. 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 the chart as illustrated by the example below. Example: WANTED: Speed for best rate of climb KNOWN: Density altitude = 5000 feet...
  • Page 133 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) 16000 14000 12000 10000 8000 6000 4000 2000 INDICATED AIRSPEED – KNOTS F03−013 (CORRECTED FOR INSTRUMENT ERROR) Figure 5–3. Speed for Best Rate of Climb FAA Approved Revision 5 5–7...
  • Page 134 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 5–5. HOVER CEILING VS GROSS WEIGHT – IN GROUND EFFECT (IGE) Description: The hover ceiling charts show the maximum hover weight capability in ground effect (IGE) for known conditions of pressure altitude and outside air temperature (OAT), or alternately, the maximum hover ceiling for a known gross weight and outside air temperature.
  • Page 135 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 136 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 137 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 138 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 139 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 140 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 141 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 1.
  • Page 142 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 1.
  • Page 143 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 1.
  • Page 144 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICA BLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET INCREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY REDUCE WEIGHT: DECREASE WEIGHT: 50 LB WITH ABRASION STRIPS ON...
  • Page 145 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50lb WITH ABRASION STRIPS ON 1.
  • Page 146 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 5–6. Height Velocity Diagram/Gross Weight Limits For Height Velocity Diagram Description: Airspeed/altitude combinations to be avoided in the event of an engine fail ure during takeoff are shown in the Height Velocity diagram (Ref. Figure 5−15).
  • Page 147 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) 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 148 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) 7000 6000 5000 4000 3000 2000 1000 2000 2200 2400 2600 2800 3000 3200 GROSS WEIGHT – POUNDS F03−016−2 Figure 5–16. Gross Weight Limits for Height Velocity Diagram FAA Approved 5–22 Revision 5...
  • Page 149 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) 5–7. POWER CHECK – ALLISON 250–C20B ENGINE 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−C20B engine producing specification power as installed in the MD 500D helicopter.
  • Page 150 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) Example: WANTED Check engine performance DATA OBTAINED DURING FLIGHT: Torque = 87.2 psig TOT = 780°C PA = 1000 feet OAT = 20°C METHOD 1. Enter the bottom right of the chart at 87.2 psig torque. Move up along the 87.2 psig torque line to the 1000 foot pressure altitude curve, move left to the 20°C OAT curve;...
  • Page 151 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Performance Data (Model 369D) AMBIENT TEMPERATURE 2000 FT PRESSURE ALTITUDE LEVEL TO READ POWER REFLECT OFF SEA LEVEL LINE 103%, CABIN HEAT & ANTI−ICE OFF SCAVENGE BLEED−OFF ELECTRICAL LOAD 10 AMPS AREA OF ENGINE TORQUE LIMIT 87.2 PSI OPERATION WITH BLEED VALVE OPEN...
  • Page 153 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Performance Data 5–8. POWER CHECK – ALLISON 250–C20R/2 The Power Check Chart shows the relationship of engine torque, turbine outlet temperature, and horsepower at various conditions of pressure altitude and OAT for an Allison 250−C20R/2 engine producing specification power as in stalled in the MD 500D helicopter.
  • Page 154 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) Example 2: WANTED: Check engine performance DATA OBTAINED DURING HOVERING: Torque = 42.0 psig TOT = 650°C PA = 8000 feet OAT = 7.5°C NOTE : Be sure to add 2.5°C to the observed OAT before continuing. Specification TOT (from chart): 645°C Compare the specification TOT of 645°C with the TOT observed during flight (650°C for this example).
  • Page 155 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Performance Data (Model 369D) ADD TO AMBIENT TEMPERATURE CABIN HEAT, ANTI−ICE OFF 2 1/2°C (4 1/2°F) IN HOVER SCAVENGE BLEED OFF 1°C (2°F) IN FORWARD FLIGHT ELECTRICAL LOAD 10 AMPS TO READ POWER REFLECT OFF SEA LEVEL LINE ACCELERATING BLEED VALVE OPEN AVOID ENGINE CHECK IN REGION...
  • Page 157 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) E C T I O N EIGHT AND ALANCE TABLE OF CONTENTS PARAGRAPH PAGE 6−1. Weight and Balance Characteristics ........6−1 Table 6−1.
  • Page 159 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) SECTION VI WEIGHT AND BALANCE DATA 6–1. WEIGHT AND BALANCE CHARACTERISTICS Weight and balance characteristics: Maximum certified gross weight − 3000 pounds. Minimum flying weight − 1538 pounds. Longitudinal Reference Datum100 inches forward of rotor centerline (rotor hub centerline is located at Station 100).
  • Page 160 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) 3000 2800 2600 2400 2200 2000 1800 1600 1538 107.4 MINIMUM FLYING WEIGHT LONGITUDINAL ARM (INCHES) F03−019 Figure 6–1. Longitudinal Center of Gravity Limits 6–2 Revision 5...
  • Page 161 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) ROTOR C L 78.5 100.0 124.0 CG OF COPILOT CARGO COMPARTMENT PASSENGER 28.0 174.0 + 13.0 + 12.2 REFERENCE DATUM –12.2 –13.0 TW0 PLACE COCKPIT CG OF PILOT LEFT HAND COMMAND 105.0 73.5...
  • Page 162 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) LATERAL ‘‘+’’ CG REFERENCE FORWARD CENTERLINE 100.0 28.0 99.0 107.4 PERMISSIBLE CG LIMITS SLING POINT OIL TANK−RH SIDE LEVELING PLUMB STA 92.6 FIRE WALL JIG POINT 3° AFT JACKING POINT STA 197.2 STA 284.0 STA 174.0...
  • Page 163 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) F02−020 Figure 6–3. Station Diagram Revision 5 6–5...
  • Page 164 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) 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 165 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) Figure 6–4. Sample Weight and Balance Report (Sheet 1 of 2) Revision 5 6–7...
  • Page 166 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) Figure 6–4. Sample Weight and Balance Report (Sheet 2 of 2) 6–8 Revision 5...
  • Page 167 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) F03−022 Figure 6–5. Sample Weight and Balance Record Revision 5 6–9...
  • Page 168 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) 6–4. WEIGHT AND BALANCE DETERMINATION – PASSENGER CONFIGURATION To determine that the gross weight and longitudinal center of gravity (fore and aft) for a given flight are within limits, proceed as follows: Obtain aircraft delivered weight and moment from the Weight and Balance Record inserted in this section.
  • Page 169 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) EXAMPLE I. Longitudinal CG Calculation – Passenger Items Weight Moment (lb) (in.–lb) Delivered Weight 1,471 160,790 Pilot 12,495 Passenger − Fwd Outboard 12,495 Passenger − Fwd Center 12,155 Passenger −...
  • Page 170 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) 6–5. LONGITUDINAL LOADING OF CARGO The large aft compartment of the Model 369D 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 171 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) EXAMPLE II. Longitudinal CG Calculation – Passenger and Cargo Weight Moment (lb) (in.–lb) Items Delivered Weight 1,471 160,790 Pilot 12,495 Passenger − Fwd Outboard 12,495 Cargo 80,800 1. Zero Fuel Weight 2,611 265,780 Add:...
  • Page 172 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) 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. All combinations of internal and external loadings are permissible if gross weight, longitudinal, and lateral center of gravity considerations permit.
  • Page 173 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) EXAMPLE III. Lateral CG Calculation – Passenger and Cargo Weight Lateral Lateral Moment Items (lb) Arm (in) (in.–lb) Delivered Weight 1,471 Pilot (L/H) −13.0 −2,210 Passenger − Fwd (R/H) +18.1 +3,077 Cargo...
  • Page 174 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) F03−023−1A Figure 6–6. Fuel Station Diagram (Jet–A at 6.8 Pounds per Gallon) (Sheet 1 of 2) 6–16 Revision 5...
  • Page 175 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) F03−023−2A Figure 6–6. Fuel Station Diagram (Jet–B at 6.5 Pounds per Gallon) (Sheet 2 of 2) Revision 5 6–17...
  • Page 176 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) Table 6–2. Weights and Longitudinal Moments – Pilot, Passenger, Baggage Pilot and Passenger Weights and Longitudinal Moments Moment Moment Moment Passenger (in.–lb) (in.–lb) (in.–lb) Weight (lb) Pilot or Fwd Center Fwd Aft Passenger R/H Passenger...
  • Page 177 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) Table 6–3. Weights and Lateral Moments – Pilot, Passenger, Baggage Moment Moment Moment Moment (in.–lb) (in.–lb) (in.–lb) (in.–lb) Pilot L/H and Passenger Passenger Passenger Aft Passenger Passenger R/H FWD Center Fwd R/H FWD R/H and L/H...
  • Page 178 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) CG OF PASSENGERS FUEL FILLER INLET LINE +12.0 IN. +5.2 IN. FWD C KIT WEIGHT = 17.9 LB KIT CG = 101.4 IN. LONGITUDINAL –12.0 IN. (–) –1.0 IN. LATERAL 109.2 124.0 95.5...
  • Page 179 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Weight and Balance Data (Model 369D) 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 6−5.
  • Page 180 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Weight and Balance Data (Model 369D) VIEW I LOOP FOR VERTICAL AND LATERAL RESTRAINT CARGO FLOOR VIEW SHOWING LOCATION OF CARGO TIEDOWN POINTS AND LOOPS − MINIMUM LOOP STRINGTH − 1800 LB VIEW II WRAP COONTAINER WITH SIMILAR STRAP SUCH THAT LOOPS CANNOT SLIP CARGO FLOOR...
  • Page 181 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Handling Servicing (Model 369D) and Maintenance E C T I O N ANDLING, ERVICING AINTENANCE TABLE OF CONTENTS PARAGRAPH PAGE 7−1. Helicopter Components ..........7−1 7−2.
  • Page 183 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 184 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance HORIZONTAL STABILIZER MAIN ROTOR INSTALLATION VERTICAL STABILIZER TAIL ROTOR TRANSMISSION FLIGHT CONTROLS INSTALLATION TAILBOOM AFT SECTION INSTALLATION TAIL ROTOR ASSEMBLY ENGINE INSTALLATION FORWARD SECTION INSTALLATION MAIN TRANSMISSION AND POWER TRAIN ENGINE ACCESS DOORS CARGO DOOR...
  • Page 185 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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.
  • Page 186 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance 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.
  • Page 187 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 188 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance 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 DOOR TIE CORD ACCESS PITOT TUBE LATCH...
  • Page 189 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 190 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance Specification Material Manufacturer 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 East Hanover, NJ 07936 Hatcol 3211 Hatco Corporation...
  • Page 191 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 192 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance Specification Material Manufacturer One−Way Lock Continued Specification Material Manufacturer MIL−PRF−6083 Brayco Micronic 783 Castrol Industrial North Amer ica Inc. Royco 783 Royal Lubricants Company, Inc. Hydraunycoil FH−6 NYCO, S.A. 9.
  • Page 193 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance OIL FILTER BYPASS INDICATOR (369F5100 M/R TRANSMISSION ONLY) TRANSMISSION OIL LEVEL SIGHT GAUGE MAIN TRANSMISSION FILLER MAIN TRANSMISSION BATTERY DRAIN VALVES LIQUID LEVEL SIGHT GAGE ONE−WAY LOCK OVERBOARD OIL RESERVOIR DRAIN LINE ENGINE ACCESSORY...
  • Page 194 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance ENGINE WASH ENGINE OIL FITTING TANK DRAIN MAIN TRANSMISSION OIL COOLER DRAIN ENGINE OIL SCAVENGE OIL FILTER COOLER DRAIN STATION 137.50 BULKHEAD OIL FILTER BYPASS INDICATOR 250−C20/R2 SP ENGINE BYPASS INDICATOR ENGINE FUEL FILTER F02−027−2...
  • Page 195 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 196 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance 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.
  • Page 197 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance Tail rotor transmission: A liquid level sight gauge for checking oil level is located on the rear of the transmission housing. Check oil level by viewing sight gauge. Servicing of the tail rotor transmission should be performed by maintenance personnel.
  • Page 198 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance 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 199 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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).
  • Page 200 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance Start engine (Ref. Section IV). After idle stabilizes, accelerate engine to 103 percent N . Operate until oil temperature shows an increase and ammeter reads zero. Shut down engine (Ref. Section IV). Replenish fuel as necessary.
  • Page 201 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance DOOR FRAME PILOT’S DOOR PASSENGER/CARGO COMPARTMENT DOOR (LH SHOWN, RH SIMILAR) FUSELAGE STRUCTURE HINGE PIN DOOR HINGE DOOR STRUCTURE F40–043 Figure 7–5. Pilot and Passenger/Cargo Door Removal Revision 5 7–19...
  • Page 202 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Handling, Servicing, (Model 369D) and Maintenance 7–19. SPECIAL OPERATIONAL CHECKS AND PROCEDURES Cleaning engine compressor: Refer to Figure 7−4 for water wash provision location (if installed). Engine compressor cleaning should be performed by qualified personnel in accordance with the HMI and the Engine Operation and Maintenance Manual.
  • Page 203 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL Handling, Servicing, (Model 369D) and Maintenance 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 205 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Additional Operations (Model 369D) and Performance Data VIII E C T I O N DDITIONAL PERATIONS ERFORMANCE TABLE OF CONTENTS PARAGRAPH PAGE 8−1. Hover Ceiling − Out of Ground Effect (OGE) ......8−1 Figure 8−1.
  • Page 207 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Additional Operations and Performance Data SECTION VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA 8–1. HOVER CEILING – OUT OF GROUND EFFECT (OGE) Select the appropriate hover performance chart for the engine CAUTION (Allison 250–C20B or 250–C20R/2) and/or optional equipment installed.
  • Page 208 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Additional Operations (Model 369D) and Performance Data THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 209 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Additional Operations and Performance Data THIS CHART BASED ON WINDS LESS THAN 3 KNOTS, CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN...
  • Page 210 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Additional Operations (Model 369D) and Performance Data THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERE, APPLICABLE TO PARTICLE SEPARATOR (SCAVENGE OFF) OR STANDARD ENGINE AIR INLET REDUCE WEIGHT: INCREASE WEIGHT: 50LB WITH ABRASION STRIPS ON MAIN 1.
  • Page 211 MD 500D CSP–D–1 ROTORCRAFT FLIGHT MANUAL (Model 369D) Optional Equipment E C T I O N PTIONAL QUIPMENT TABLE OF CONTENTS PARAGRAPH PAGE 9−1. General Information ..........9−1 9−2.
  • Page 212 CSP–D–1 MD 500D ROTORCRAFT FLIGHT MANUAL (Model 369D) Optional Equipment PARAGRAPH PAGE 9−9. Operating Instructions − Engine Air Inlet Diverter ..... . . 9−37 Figure 9−11.
  • Page 213 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Optional Equipment SECTION IX OPTIONAL EQUIPMENT 9–1. GENERAL INFORMATION This section provides general supplemental information on optional equipment for the MD 500D Helicopter. The information includes a listing of usable op tional equipment and compatibility of combined equipment on the helicopter. Supplemental data is prepared and included in this section whenever the in stallation of that equipment affects the FAA Approval Data for Limitations (Section II), Emergency and Malfunction Procedures (Section III), Normal Pro...
  • Page 214 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Table 9–1. Optional Equipment – Model 369D Helicopter (250–C20B or C20R/2) Publication Equipment *Pitot heat CSP−D−1 *Extended landing gear CSP−D−1 *Rotor brake CSP−D−1 *Engine air particle separator filter − APM filter CSP−D−1 Cargo hook CSP−D−1 Section IX...
  • Page 215 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Optional Equipment 9–4. COMPATIBILITY – COMBINED OPTIONAL EQUIPMENT Table 9–3. Optional Equipment Compatibility – Model 369D Helicopter Compatibility: Blank=Yes; X=No: (x)=Installable/Not usable Optional Part Number Equipment (369H/369D) Emergency Floats 369D290121−501, −505, −507, −515, −517, −519 Litter Kit 369H90011...
  • Page 217 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) Optional Equipment Cargo Hook Kit 9–5. OPERATING INSTRUCTIONS: CARGO HOOK KIT PART I GENERAL The MDHI 369H90072−501 and −507 Cargo Hook Kit consists of a cargo hook which attaches 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 218 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Cargo Hook Kit PART II LIMITATIONS Weight Limitations: Maximum takeoff and landing gross weight 3000 pounds. Weight CAUTION in excess of 3000 pounds must be external and jettisonable. Maximum Rotorcraft − Load Combinations operating gross weight 3550 pounds (FAR 133).
  • Page 219 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 220 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) 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 221 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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. Cargo hook keeper should permit easy entrance into throat.
  • Page 222 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Cargo Hook Kit EXTERNAL RELEASE (TURN CLOCKWISE) ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK (LOAD BEAM) F02−029 Figure 9–3. Cargo Hook PART V PERFORMANCE DATA Refer to Section V for IGE hover performance or Section VIII for OGE hover performance to assist in planning operations with the cargo hook.
  • Page 223 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 (Model 369D) 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 225 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) 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 226 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Anti–Ice Airframe Fuel FIlter PART II LIMITATIONS Altitude limitations: If ground temperature prior to flight is 5°C or less, flight operations are limited to 12,000 feet pressure altitude maximum. If ground temperature prior to flight is above 5°C, flight operations are lim ited to 14,000 feet pressure altitude maximum, but not to exceed limitations of Section II.
  • Page 227 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Anti–Ice Airframe Fuel FIlter PART IV NORMAL PROCEDURES Preflight checks: Battery switch − BATTERY or EXT PWR Start Pump − ON Do not open drain valve unless start pump is ON. An unexpected WARNING flameout or power loss may occur if air is allowed to enter the fuel system.
  • Page 228 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Anti–Ice Airframe Fuel FIlter System operation check: With BATTTERY or EXT PWR on, verify that FUEL ANTI−ICE circuit breaker is IN and the dimming switch is in the BRT position (Ref. Figure 9−5).
  • Page 229 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Four–Bladed Tail Rotor 9–7. OPERATING INSTRUCTIONS: FOUR–BLADED TAIL ROTOR PART I GENERAL The MDHI Four−Bladed Tail Rotor Kit has been developed to reduce the exter nal noise signature of the helicopter. It consists of two principal assemblies, a four bladed tail rotor, and gearbox.
  • Page 230 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Four–Bladed Tail Rotor PART II LIMITATIONS Flight restrictions: NOTE : MD 500D (Model 369D) helicopters equipped with the Allison 250–C20R/2 engine and the four–bladed tail rotor kit are approved in combination only with the optional equipment depicted in Section IX, Table 9–1.
  • Page 231 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Four–Bladed Tail Rotor PART III EMERGENCY AND MALFUNCTION PROCEDURES ENGINE FAILURE Conditions: In flight. Procedures: Allow the speed to reduce to 131 knots IAS or lower (see V placard). Maintain rotor speed between 415 and 523 RPM by use of collective con trol.
  • Page 232 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Four–Bladed Tail Rotor Low speed maneuvering: Certain maneuvers may cause extreme T/R flapping and pounding CAUTION of the T/R teetering stop support portion of the retaining nut (felt and heard by the pilot as a momentary medium frequency vibration). These maneuvers usually involve rapid yaw rates that allow the T/R to pass through the relative wind line.
  • Page 233 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Four–Bladed Tail Rotor PART VI WEIGHT AND BALANCE DATA Weight and balance characteristics: See Table 9−4 and Figure 9−6 and Figure 9−7 for CG limits. Table 9–4. Center of Gravity Limits Gross Weight Longitudinal C.G.
  • Page 234 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Four–Bladed Tail Rotor 3000 2800 2600 2400 2200 2000 1800 1600 1592 LB 108.1 LONGITUDINAL ARM − INCHES F02−014 Figure 9–6. Longitudinal Center of Gravity Limits FAA Approved 9–22 Revision 5...
  • Page 235 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Four–Bladed Tail Rotor 3000 FORWARD 2800 2600 (−) LEFT (+) RIGHT AIRCRAFT LATERAL LATERAL CENTERLINE CG LIMIT CG LIMIT 2400 2200 2000 1800 1600 1592− 1500 −5 −4 −3 −2 −1 −1.7 +1.7...
  • Page 236 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Four–Bladed Tail Rotor PART VII HANDLING SERVICING AND MAINTENANCE Servicing materials for the 4−bladed tail rotor transmission are the same as the 2−bladed tail rotor transmission (Ref. Section VII). PART VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA Refer to Section VIII for OGE hover performance data.
  • Page 237 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats 9–8. OPERATING INSTRUCTIONS – EMERGENCY FLOATS PART I GENERAL MDHI Emergency Float Kit, consists of inflatable bag−type floats intended for use in emergency landings only, during over−water operation. It is furnished with squib−actuated valves and with steel pressure vessels.
  • Page 238 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 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 239 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats Gross weight limitations: Maximum gross weight is 3000 pounds. Minimum gross weight is 1680 pounds. Center of gravity limits: Longitudinal C.G. Limit Lateral C.G. Limit (Sta−in.) (Sta−in.) Gross Weight (lb) Forward Aft* (−) Left, (+) Right...
  • Page 240 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats EMER FLOATS – INFLATED IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 1680 TO 3000 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 22K (85K MIN);...
  • Page 241 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats FLOATS STOWED IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2001 TO 2500 LB °C –30 –20 –10 NO FLIGHT SQUIB VALVE FOR AUTOROTATION V REDUCE SPEED BY 25K (90K MIN);...
  • Page 242 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats 250 – C20R/2 EMER FLOATS – INFLATED IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 1680 TO 3000 LB ° –30 –20 –10 NO FLIGHT SQUIB VALVE FOR AUTOROTATION V REDUCE SPEED BY 25K (85K MIN);...
  • Page 243 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats 250 – C20R/2 FLOATS STOWED IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2001 TO 2500 LB ° –30 –20 –10 NO FLIGHT SQUIB CONFIG. FOR AUTOROTATION V REDUCE SPEED BY 25K (95K MIN);...
  • Page 244 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats PART III EMERGENCY AND MALFUNCTION PROCEDURES EMERGENCY FLOAT INFLATION If emergency occurs at airspeeds greater than maximum CAUTION permissible float inflation speed, i.e., 81 knots IAS at less than 6,000 feet altitude, 77 knots IAS at 6,000 feet altitude and above, reduce speed to an appropriate value prior to float inflation.
  • Page 245 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 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. Figure 9−10).
  • Page 246 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats In−flight float inflation data: Float inflation time and altitude required for deployment are presented be low. Time is affected by temperature. Deployment altitude is based on a sta bilized autorotational rate of descent of 1800 feet per minute.
  • Page 247 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Emergency Floats PART V PERFORMANCE DATA Hover Performance with Stowed Floats No change from that of the basic helicopter with extended landing gear. PART VII HANDLING SERVICING AND MAINTENANCE Inspection and functional checks of the emergency float system should be con ducted in accordance with applicable installation instructions.
  • Page 249 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Engine Air Inlet Diverter 9–9. OPERATING INSTRUCTIONS – ENGINE AIR INLET DIVERTER PART I GENERAL The MDHI Engine Air Inlet Diverter Kit (either 1 or 2 piece) inhibits ingesting foreign objects into the engine air inlet which might be of sufficient mass to puncture the inlet screen/particle separator and damage the engine.
  • Page 250 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Engine Air Inlet Diverter PART II LIMITATIONS Environmental operating conditions: Maximum operating OAT is 28°C at sea level, with 2.0°C per 1000 feet lapse rate. Airspeed limits: is limited to 125 knots IAS or less (Ref. Figure 9−1 1). is limited to 100 knots IAS or less during autorotation (Ref.
  • Page 251 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Engine Air Inlet Diverter IAS (KTS) INLET DIVERTER PRESS ALT X 1000 GROSS WT = 2001 TO 2500 LB ° –30 120 115 –20 122 117 –10 NO FLIGHT FOR AUTOROTATION VNE REDUCE SPEED BY 25K (95K MIN);...
  • Page 252 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Engine Air Inlet Diverter PART III EMERGENCY AND MALFUNCTION PROCEDURES AIR RESTART − ENGINE Procedures: Follow the emergency air restart procedure described in Section III. Recommended pressure altitude is 11,000 feet or below. PART IV NORMAL PROCEDURES Cruise:...
  • Page 253 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Utiltiy Floats 9–10. OPERATING INSTRUCTIONS – UTILITY FLOATS PART I GENERAL The MDHI Utility Float Kit is designed to facilitate operation of the helicopter from both land and water. The kit consists of two multicell bag type floats, two aft skid tube extensions, two sets of stabilizing surfaces, and the necessary hardware for attachment.
  • Page 254 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Utiltiy Floats PART II LIMITATIONS Float inflation pressure: Minimum float operational pressure is 2.0 psig. Types of operation: Night flight over water beyond autorotation capability to ground is prohib ited, unless Night Landing Lighting Kit is installed . Takeoff and landing on water at night is prohibited, unless Night Landing Lighting Kit is installed.
  • Page 255 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Utiltiy Floats NOTE : To account for anticipated variations in ambient temperature or water temperature at a scheduled landing site, the following procedure should be used to maintain the minimum 2. 0 psig inflation pressure. For ambient (air) temperature or water temperature colder than the temperature at initial inflation, float inflation pressure should be increased 0.5 psig (above) the minimum 2.0 psig) for each 15°F decrease in temperature anticipated.
  • Page 256 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Utiltiy Floats UTILITY FLOATS IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2000 OR LESS ° –30 130 125 120 115 110 –20 122 110 –10 125 100 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 2K (85K MIN);...
  • Page 257 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Utiltiy Floats UTILITY FLOATS IAS (KNOTS) PRESS ALT X 1000 GROSS WT = 2501 TO 3000 ° –30 130 125 108 –20 118 100 –10 129 106 118 100 130 109 119 101 132 110 NO FLIGHT...
  • Page 258 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Utiltiy Floats PART III EMERGENCY AND MALFUNCTION PROCEDURES AUTOROTATIONAL LANDING Procedures: Make a normal autorotational approach. Minimize forward speed prior to water contact. Recommended water contact speed 10 knots or less. Do not lower collec tive until forward speed is 5 knots or less.
  • Page 259 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Utiltiy Floats Water taxiing: Water taxi speed should be less than 10 knots. It will be necessary to use some collective pitch to taxi at greater than 5 knots. Some collective pitch may be required under certain conditions to stop heli copter during water taxi.
  • Page 260 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Utiltiy Floats SMOOTH HARD SURFACE OR CALM WATER WIND CALM AVOID OPERATION IN CROSS−HATCHED AREAS Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î Î...
  • Page 261 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) Utiltiy Floats INDICATED AIRSPEED − KNOTS (CORRECTED FOR INSTRUMENT ERROR) F02−032 Figure 9–14. Airspeed Calibration Curve – Utility Floats Installed FAA Approved Revision 5 9–49...
  • Page 262 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D Optional Equipment (Model 369D) Utiltiy Floats PART VII HANDLING SERVICING AND MAINTENANCE Inspection and functional checks of the utility float system should be conducted in accordance with applicable installation instructions. PART VIII ADDITIONAL OPERATIONS AND PERFORMANCE DATA Refer to Section VIII for OGE hover performance charts.
  • Page 263 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369H9001 Litter Kit 9–11. OPERATINIG INSTRUCTIONS: 369H9001 LITTER KIT PART I GENERAL The MDHI Litter Kit has been designed to facilitate rapid conversion of the helicopter to an air ambulance configuration. The Litter Kit provides for trans porting one or two litter patients as well as one or two attendants in the cargo compartment of the helicopter.
  • Page 264 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D (Model 369D) Optional Equipment 369H9001 Litter Kit PART II LIMITATIONS Litters Installed Configuration: With litters installed, operations must be conducted with the 369H92733 bubble glass window panels installed. Observe the airspeed limits depicted on the V placard (Ref.
  • Page 265 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369H9001 Litter Kit PART IV NORMAL PROCEDURES Restraining belts for litter occupants should be secure prior to flight. Belts are to be installed with the fixed length, PN 369H6511−11; −13 (with buckle) at tached to the outboard fitting, on each side of helicopter.
  • Page 266 CSP–D–1 ROTORCRAFT FLIGHT MANUAL MD 500D (Model 369D) Optional Equipment 369H9001 Litter Kit 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 INDICATED AIRSPEED − KNOTS (CORRECTED FOR INSTRUMENT ERROR) F02−040 Figure 9–16. Speed For Best Rate of Climb FAA Approved 9–54 Revision 5...
  • Page 267 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369H9001 Litter Kit PART VI WEIGHT AND BALANCE DATA ITEM WEIGHT Longitudinal C.G. Lateral C.G. (Lbs.) (inches) Inches Litter Kit − without special doors 52.8 93.1 Special doors with bubble windows (2)** 41.2 98.2 Special doors with standard windows (2)**...
  • Page 269 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Hoist 9–12. OPERATING INSTRUCTIONS: HOIST PART I GENERAL The MDHI Hoist No. 369H90070−521 (left side installation), −522 (right side installation) is a fixed position, electrically operated unit; the left hand instal lation applies to aircraft with a right hand pilot station and the right hand installation applies to aircraft with a left hand pilot station.
  • Page 270 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Hoist PART II LIMITATIONS Weight Limitations: Maximum gross weight, including load on hoist, is 3000 pounds. Minimum flying weight, no load on hoist, is 1538 pounds. NOTE : Ballast must be added as required to meet minimum flying weight of 1538 pounds.
  • Page 271 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Hoist Placards: Make placards stating approved load class(es) and occupancy limitations; display placards in conspicuous location in cabin. ‘‘External Load Limit 300 Pounds’’ installed on the hook. NOTE : 300 pounds is the allowable loading limit on the hoist hook. Minimum Flight Crew: For hoist operation, minimum flight crew is two, consisting of pilot and hoist operator.
  • Page 272 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Hoist PART IV NORMAL PROCEDURES Normal Operation: Check hoist circuit breaker IN. Check cable cut circuit breaker IN. Hoist operator must wear an approved safety harness (provided with hoist) during all hoisting operations. While in hover regime over hoist operations site, bring the hook over the door as the door is opened, slide the bar latch into door slot to lock door in open position.
  • Page 273 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Hoist R/H HOIST KIT (STOWED) L/H HOIST KIT (STOWED) INDICATED AIRSPEED − KNOTS (CORRECTED FOR INSTRUMENT ERROR) F02−033 Figure 9–17. Airspeed Calibration Curve with Hoist Kit Installed FAA Approved Revision 5 9–61...
  • Page 274 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Hoist PART VI WEIGHT AND BALANCE DATA The following tables should be used by the operator as a guide to determine the maximum hoist load which permits operation within the certificated center of gravity envelope.
  • Page 275 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Hoist Table 9–6. Weights/Centers of Gravity – Hoist Installations Longitudinal C.G. Lateral C.G. (Inches) (Inches) Weight Weight Item (Pounds) 369H90070−513 82.6 82.6 −3.7 −3.7 Provisions 369H90070−521 30.8 − 100.6 − −24.4 Assembly 369H90070−522...
  • Page 276 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Hoist Table 9–7. Permissible Right Hand Hoist Loads* Forward Attendant Weight (Pounds) Passenger Pilot Weight Weight Weight (Pounds) (Pounds) (Pounds) Permissible Hoist Loads (Pounds) *Permissible hoist load may be increased 9 pounds for each 10 pounds of ballast or passenger weight placed at seat location opposite hoist load during hoisting operations to 300 pounds maximum.
  • Page 277 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Hoist Table 9–8. Permissible Left Hand Hoist Loads* Forward Attendant Weight (Pounds) Passenger Pilot Weight Weight Weight (Pounds) (Pounds) (Pounds) Permissible Hoist Loads (Pounds) *Permissible hoist load may be increased 9 pounds for each 10 pounds of ballast or passenger weight placed at seat location opposite hoist load during hoisting operations to 300 pounds maximum.
  • Page 278 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D Optional Equipment (Model 369D) Hoist LOADING EXAMPLES Right Hand Hoist NUMBER 1: Pilot = 175 Pounds Attendant Weight = 175 Pounds Forward Passenger Weight = 175 Pounds Find: Permissible Hoist Load = ??? Refer to Table 9−7, Part B for given weights. The maximum allowable hoist load is 251 pounds.
  • Page 279 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit 9–13. OPERATING INSTRUCTIONS: 369D290170 LITTER KIT PART I GENERAL The MDHI 369D290170 Litter Kit has been designed to facilitate rapid conver sion of the helicopter to an air ambulance configuration. The Litter Kit pro vides for transporting o or two litter patients as well as o or two atten...
  • Page 280 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit PART II LIMITATIONS Litters installed configuration: With litters installed, operations must be conducted with the doors in the extended position, and limitations C through G apply. When the attendant seat/seats (PN 369D290233) are installed, seat belts and shoulder harnesses (PN 369H92252 and 369H9513 respectively) must be installed.
  • Page 281 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit Minimum power off rotor speed: With the litter kit installed, the minimum power off main rotor rpm is 430. NOTE : When the litter kit door bubbles are installed, install red radial line 1/16 by 1/4 inch on the glass face of the rotor tachometer at 430 rpm.
  • Page 282 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit LITTER KIT IAS (KNOTS) BUBBLES EXTENDED PRESS ALT X 1000 GROSS WT = 1775 TO 2000 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 18.K (85 K MIN);...
  • Page 283 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit LITTER KIT IAS (KNOTS) BUBBLES EXTENDED PRESS ALT X 1000 GROSS WT = 2501 TO 3000 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 6 K (95 K MIN);...
  • Page 284 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit LITTER KIT IAS (KNOTS) BUBBLES RETRACTED PRESS ALT X 1000 GROSS WT = 2001 TO 2500 LB ° –30 –20 –10 NO FLIGHT FOR AUTOROTATION V REDUCE SPEED BY 23 K (90 K MIN);...
  • Page 285 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit PART IV NORMAL PROCEDURES Restraining belts provided for litter occupants should be secure prior to flight. Belts are to be installed with the fixed length, PN 369H6511−11, −13 (with buckle) attached to the outboard fitting, on each side of helicopter.
  • Page 286 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit STRAP ASSEMBLIES LATCHES SECOND FIRST LITTER LITTER F02−034 Figure 9–20. Litters in Position FAA Approved 9–74 Revision 5...
  • Page 287 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit STRAP ASSEMBLIES SECURED F02−035 Figure 9–21. Litters Secured FAA Approved Revision 5 9–75...
  • Page 288 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit STOWAGE BRACES SUPPORT ARM ASSEMBLIES (LOCKED POSITION) F02−036 Figure 9–22. Stowage Bags and Components FAA Approved 9–76 Revision 5...
  • Page 289 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit ATTENDANT SEATS STOWAGE BAG AND STOWED COMPONENTS ATTENDANT SEAT STRAP ASSEMBLIES LITTER KIT STRAP ASSEMBLIES EYEBOLT BRACES (STOWED) F02−037 Figure 9–23. Litter Kit Components Stowed FAA Approved Revision 5 9–77...
  • Page 290 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit Installation: Litter doors are spring–loaded. When opening doors stand clear CAUTION to avoid coming in contact with opening action of doors. Open litter doors for access to litter kit. Release strap assemblies securing stowage bag and litters to cargo floor.
  • Page 291 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit Position litter on arm support and slide litter to engage latching on support arm (Ref Figure 9−24). With litters in position rotate handle to engage latching mechanism. NOTE : If handle does not latch, rotate counterclockwise to loosen.
  • Page 292 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit PART V PERFORMANCE DATA Speed for Best Rate of Climb: The variation of speed for best rate of climb with altitude is shown on Figure 9−26. Hover Performance: The hover performance is reduced by 15 pounds when the litter kit is installed.
  • Page 293 MD 500D ROTORCRAFT FLIGHT MANUAL CSP–D–1 Optional Equipment (Model 369D) 369D290170 Litter Kit 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 INDICATED AIRSPEED − KNOTS (CORRECTED FOR INSTRUMENT ERROR) F02−040 Figure 9–26. Speed For Best Rate of Climb FAA Approved Revision 5 9–81...
  • Page 294 ROTORCRAFT FLIGHT MANUAL CSP–D–1 MD 500D (Model 369D) Optional Equipment 369D290170 Litter Kit PART VI WEIGHT AND BALANCE DATA Weight Longitudinal Item (pounds) C.G. (inches) Litter Kit* 141.0 96.3 *Part No. 369D290170 Aircraft loadings with litter are permissible for as many as seven persons (based on 170 pounds each), provided the gross weight of 3000 pounds is not exceeded.
  • Page 295 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Main Rotor Blade Abrasion Tape 9–14. MAIN ROTOR BLADE ABRASION TAPE PART I GENERAL The MDHI main rotor blade abrasion tape kit, Part No. 369D21104, is recommended for blades which are subject to a highly abrasive environment. Installation of the stainless steel abrasion tape to the leading edge of the main rotor blade (Ref.
  • Page 296 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 (Model 369D) Optional Equipment Main Rotor Blade Abrasion Tape THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERES. APPLICABLE TO STANDARD INLET AND PARTICLE SEPARATOR WITH SCAVENGE OFF. REDUCE WEIGHT BY 60 POUNDS WITH SCAVENGE ON.
  • Page 297 ROTORCRAFT FLIGHT MANUAL MD 500D CSP–D–1 Optional Equipment (Model 369D) Main Rotor Blade Abrasion Tape THIS CHART BASED ON CABIN HEAT, ENGINE ANTI−ICE OFF, ELECTRICAL LOAD 10 AMPERES. APPLICABLE TO STANDARD INLET AND PARTICLE SEPARATOR WITH SCAVENGE OFF. REDUCE WEIGHT BY 60 POUNDS WITH SCAVENGE ON.

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