MD Helicopters 369E Rotorcraft Flight Manual Download

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CSP

−

Emergency and

Malfunction Procedures

ROTORCRAFT FLIGHT MANUAL

MD 500E

(Model 369E)

Revision 14

−

FAA Approved

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10. MAIN ROTOR AND TAIL ROTOR TRANSMISSION MALFUNCTIONS

M/R TRANSMISSION OIL PRESSURE

Indications:

Red

XMSN

OIL

PRESS

indicator ON.

Conditions:

Transmission oil pressure low.

Procedures:

Land as soon as possible.

M/R TRANSMISSION OIL TEMPERATURE

Indications:

Red

XMSN

OIL

TEMP

indicator ON.

Conditions:

Transmission oil temperature exceeds maximum limit.

Procedures:

Land as soon as possible.

M/R TRANSMISSION CHIP DETECTOR

Indications:

Yellow

M/R

XMSN

CHIPS

indicator ON.

Conditions:

Metal contamination of oil.

Procedures:

Land as soon as possible.

TAIL ROTOR TRANSMISSION CHIP DETECTOR

Indications:

Yellow

T/R

XMSN

CHIPS

indicator ON.

Conditions:

Metal contamination of oil.

Procedures:

Land as soon as possible.

Summary of Contents for 369E

Page 1: ...F03 001 R O T O R C R A F T F L I G H T M A N U A L REGISTRATION NO _________________ SERIAL NO _________________ MD 500E Cover ...

Page 2: ......

Page 3: ...II OF THIS MANUAL AND ANY ADDITIONAL LIMITATIONS FROM SECTION IX AS A RESULT OF AN INSTALLED OPTIONAL EQUIPMENT ITEM SECTIONS III IV AND V CONTAIN RECOMMENDED PROCEDURES AND DATA AND ARE FAA APPROVED THE AIRWORTHINESS LIMITATIONS 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 MD 500E Type Certificate No H3WE Approved By_______...

Page 4: ...90 Revision 6 4 May 1990 Revision 7 1 April 1992 Revision 8 17 July 1995 Revision 9 19 March 1998 Revision 9 first part of reissue 1 Revision 10 17 April 1998 Revision 10 final part of reissue 1 Revision 11 30 December 1999 Revision 12 10 October 2000 Revision 13 22 March 2001 Revision 14 3 October 2003 Revision 15 4 October 2006 Revision 16 21 Mar 2007 Manager Flight Test Branch ANM 160L Federal ...

Page 5: ...CSP E 1 ROTORCRAFT FLIGHT MANUAL MD 500E Model 369E F iii F iv blank Revision 13 APPROVING AUTHORITIES ...

Page 6: ......

Page 7: ...ot s Briefing 1 2 1 6 Organization 1 2 1 7 Method of Presentation 1 4 1 8 Definition of Terms 1 4 1 9 Abbreviations 1 5 1 10 Technical Publications 1 7 1 11 Design and Construction 1 8 1 12 Electrical System 1 11 1 13 Auto Reignition System 1 12 1 14 Capacities and Dimensions 1 13 1 15 Conversion Charts and Tables 1 15 Section II Limitations 2 1 Flight Restrictions 2 1 2 2 Environmental Operating ...

Page 8: ...d 3 7 3 6 Emergency Landing Procedures 3 7 3 7 Fire 3 9 3 8 Engine FUEL Control System Malfunctions 3 14 3 9 Other Engine Caution Indications 3 16 3 10 Main Rotor and Tail rotor Transmission Malfunctions 3 17 3 11 Flight Control Malfunctions 3 18 3 12 Abnormal Vibrations 3 22 3 13 Fuel System Malfunctions 3 22 3 14 Electrical System Malfunctions 3 24 3 15 Other Malfunctions 3 26 3 16 Emergency Egr...

Page 9: ...limb 5 6 5 5 Hover Ceiling VS Gross Weight In ground Effect IGE 5 8 5 6 Height Velocity Diagram Gross Weight Limits For Height Velocity Diagram 5 20 5 7 Power Check Rolls Royce 250 C20B Engine 5 23 5 8 Power Check Rolls Royce 250 C20R 2 5 27 Section VI Weight and Balance Data 6 1 Weight and Balance Characteristics 6 1 6 2 Weight and Balance Criteria 6 6 6 3 Equipment Removal or Installation 6 6 6 ...

Page 10: ...s 7 16 7 16 Preservation and Storage 7 17 7 17 Flyable Storage No Time Limit 7 17 7 18 Cockpit Door Removal and Installation 7 18 7 19 Special Operational Checks and Procedures 7 20 Section VIII Additional Operations and Performance Data 8 1 Hover Ceiling Out of Ground Effect OGE 8 1 Section IX Optional Equipment 9 1 General Information 9 1 9 2 Listing Optional Equipment 9 1 9 3 Optional Equipment...

Page 11: ...II pages marked C indicate FAA approved color pages Black and white reproductions of color pages are not considered to be FAA Approved REVISION NUMBER REMARKS Revision 16 Section I Paragraph 1 3 Updated FAA ICAO aircraft type designa tor Section II Paragraphs 2 7 and 2 8 Added power turbine speed avoid range Section IV Paragraph 4 4 and 4 9 added NOTE referring to power turbine speed avoid range ...

Page 12: ... F v Revision 14 F vi Revision 14 F vii Revision 14 F viii Revision 14 F ix Revision 16 F x Revision 16 F xi Revision 16 F xii Revision 14 F xiii Revision 16 F xiv Revision 14 F xv Revision 14 F xvi Revision 14 F xvii F xviii blank Revision 14 I 1 i 1 ii blank Revision 14 1 1 Revision 16 1 2 Revision 14 1 3 Revision 14 1 4 Revision 14 1 5 Revision 14 1 6 Revision 14 1 7 Revision 14 1 8 Revision 14...

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

Page 14: ...sion 14 3 7 Revision 14 3 8 Revision 14 3 9 Revision 14 3 10 Revision 14 3 11 Revision 14 3 12 Revision 14 3 13 Revision 14 3 14 Revision 14 3 15 Revision 14 3 16 Revision 14 3 17 Revision 14 3 18 Revision 14 3 19 Revision 14 3 20 Revision 14 3 21 Revision 14 3 22 Revision 14 3 23 Revision 14 3 24 Revision 14 3 25 Revision 14 3 26 Revision 14 3 27 2 28 blank Revision 14 IV 4 i 4 ii blank Revision ...

Page 15: ...4 10 Revision 13 4 11 Revision 13 4 12 Revision 13 4 13 Revision 13 4 14 Revision 13 4 15 Revision 13 4 16 Revision 14 4 17 Revision 16 4 18 Revision 13 4 19 Revision 13 4 20 Revision 13 4 21 Revision 13 4 22 Revision 13 4 23 Revision 13 4 24 Revision 16 4 25 Revision 13 4 26 Revision 13 4 27 Revision 13 4 28 Revision 13 4 29 4 30 blank Revision 13 V 5 i Revision14 5 ii Revision14 5 1 Revision14 5...

Page 16: ...on14 5 11 Revision14 5 12 Revision14 5 13 Revision14 5 14 Revision14 5 15 Revision14 5 16 Revision14 5 17 Revision14 5 18 Revision14 5 19 Revision14 5 20 Revision14 5 21 Revision14 5 22 Revision14 5 23 Revision14 5 24 Revision14 5 25 5 26 blank Revision14 5 27 Revision14 5 28 Revision14 5 29 5 30 blank Revision14 VI 6 i 6 ii blank Revision14 6 1 Revision14 6 2 Revision14 6 3 Revision14 6 4 Revisio...

Page 17: ...evision14 6 14 Revision14 6 15 Revision14 6 16 Revision14 6 17 Revision14 6 18 Revision14 6 19 Revision14 6 20 Revision14 6 21 Revision14 6 22 Revision14 6 23 6 24 blank Revision14 VII 7 i 7 ii blank Revision14 7 1 Revision14 7 2 Revision14 7 3 Revision14 7 4 Revision14 7 5 Revision14 7 6 Revision14 7 7 Revision14 7 8 Revision 14 7 9 Revision 14 7 10 Revision 14 7 11 Revision 14 7 12 Revision14 7 ...

Page 18: ...14 VIII 8 i 8 ii blank Revision 14 8 1 Revision 14 8 2 Revision 14 8 3 Revision 14 8 4 Revision 14 IX 9 i Revision 14 9 ii Revision 14 9 1 Revision 14 9 2 Revision 14 9 3 9 4 blank Revision 14 9 5 Revision 14 9 6 Revision 14 9 7 Revision 14 9 8 Revision 14 9 9 Revision 14 9 10 Revision 14 9 11 9 12 blank Revision 14 9 13 Revision 14 9 14 Revision 14 9 15 Revision 14 9 16 Revision 14 9 17 Revision ...

Page 19: ... 9 24 Revision 14 9 25 Revision 14 9 26 Revision 14 9 27 Revision 14 9 28 Revision 14 9 29 Revision 14 9 30 Revision 14 9 31 Revision 14 9 32 Revision 14 9 33 Revision 14 9 34 Revision 14 9 35 Revision 14 9 36 Revision 14 9 37 Revision 14 9 38 Revision 14 9 39 Revision 14 9 40 Revision 14 9 41 Revision 14 9 42 Revision 14 9 43 Revision 14 9 44 Revision 14 9 45 Revision 14 9 46 Revision 14 9 47 Rev...

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Page 21: ...em 1 12 1 14 Capacities and Dimensions 1 13 Table 1 1 Fuel System Standard Non Self Sealing Fuel Tanks 1 13 Table 1 2 Fuel System Optional Self Sealing Fuel Tanks 1 13 Figure 1 1 MD 500E Principal Dimensions Standard Landing Gear 1 14 1 15 Conversion Charts and Tables 1 15 Figure 1 2 Speed MPH Knots KmH 1 15 Figure 1 3 Temperature Conversion Chart 1 16 Table 1 3 Liquid Measure U S Gallons to Liter...

Page 22: ......

Page 23: ...fied by the Federal Aviation Administration under FAA Type Certificate Number H3WE Certification of the aircraft has been accomplished in accordance with all appli cable United States Department of Transportation Federal Aviation Adminis tration Regulations in the normal helicopter category The FAA model designation is Model 369E The FAA ICAO aircraft type designator is H500 The MDHI commercial de...

Page 24: ...st of Effective Pages By referring to the Log of Revisions By Date the pilot may review a chro nological listing of changes to the Flight Manual Reading the Summary of Revisions will inform the pilot of what changes have been made by paragraph reference This summary contains only the latest Flight Manual change The List of Effective Pages allows the pilot quick reference to page numbers and their ...

Page 25: ...on are the original weight and balance report and equipment list equipment both required and optional installed on the aircraft at the time of licensing SECTION VII AIRCRAFT HANDLING SERVICING AND MAINTENANCE The information contained in this section is extracted from the Handbook of Maintenance Instructions and is highly selective The subjects chosen are those with which the pilot may have direct...

Page 26: ...ticular operation A black change bar l in the page margin designates the latest new or changed information appearing on that page A hand points to changes in the contents of an illustration 1 8 DEFINITION OF TERMS The concepts of procedural word usage and intended meaning that have been adhered to in preparing this manual is as follows Shall has been used only when the application of a procedure i...

Page 27: ...ers COM Communication CCW Counter Clockwise CW Clockwise D dBA Decibel A weighted DC Direct Current DIR Direction Directional E EGT Exhaust Gas Temperature ENG Engine EXT Extend External F F Fahrenheit FAA Federal Aviation Administration FAR Federal Aviation Regulation FS Fuselage Station Ft Foot Feet G GAL Gallons GCU Generator Control Unit GEN Generator GPU Ground Power Unit GW Gross Weight H HD...

Page 28: ...r Millibar Min Minutes MPH Miles Per Hour N N1 Gas Producer Speed N2 Power Turbine Speed NAV Navigation NR Rotor Speed O OAT Outside Air Temperature OGE Out of Ground Effect P PNL Panel POSN Position PRI Primary PRESS Pressure PSI Pounds per Square Inch PWR Power Q QTY Quantity R R Right RPM Revolutions per Minute RTR Rotor S Sec Seconds SEL Sound Exposure Level SHP Shaft Horsepower SL Sea Level S...

Page 29: ... Effective Pages that accom panies each revision identifies all affected pages Such pages must be removed from the manual and discarded Added or replaced pages must be put in and examined against the List of Effective Pages Reissues Occasionally the manual may be reissued and is identified as Reissue 1 Reissue 2 etc The preceding issue of the manual then becomes ob solete and must be discarded Thi...

Page 30: ...ucture is egg shaped and provides very clean aerodynamic lines The rigid three dimensional truss type structure increases crew safe ty by means of its roll bar design and by reduction in the number of poten tial sources of failure The airframe structure is designed to be energy ab sorbing and fails progressively in the event of impact The fuselage is a semi monocoque structure that is divided into...

Page 31: ... pilot seated on the left side of the cockpit The passengers sit to the right abreast of the pilot Seat belts are provided for all positions In the military version the center seat is eliminated An instrument panel is located forward of the seat at the aircraft center line The panel incorporates standard flight and engine instruments in addi tion to warning and caution lights The panel also contai...

Page 32: ... is mounted on the aft end of the tailboom and has a self contained lubricant system The tail rotor is mounted on the out put shaft of the transmission and consists of two variable pitch blades Main rotor system The helicopter utilizes a five bladed fully articulated main rotor assembly with unique features While contemporary helicopters use torsion tension straps in lieu of thrust bearing stacks ...

Page 33: ...utilized an air ground switch to disable the ENGINE OUT low rotor audio warning while on the ground and a three position RE IGN test switch that in addition to testing the reignition system also tested the ENGINE OUT low rotor audio warning This early generic version was delivered on aircraft serial numbers 384E through 508E On aircraft serial numbers 509E and subsequent a modified late generic ve...

Page 34: ...otor warning On Aircraft equipped with the original pre generic electrical system the ig nitor will stop firing once the N1 and NR increase above 55 N1 468 NR On aircraft equipped with a generic wire harness style electrical system the ignitor will also continue to fire until the RE IGN P RST caution light is reset NOTE In the event of a NR or N1 tach generator failure the RE IGN P RST caution lig...

Page 35: ...7 2 1 6 1 9 12 5 5 7 Total 242 53 3 64 0 416 0 188 7 Table 1 2 Fuel System Optional Self Sealing Fuel Tanks Fuel Type Liters Imp Gal U S Gal Pounds Kilograms Jet A Usable 226 8 49 9 59 9 407 0 184 9 Unusable 7 9 1 7 2 1 14 3 6 5 Total 234 7 51 6 62 0 421 3 190 8 Jet B Usable 226 8 49 9 59 9 389 4 176 7 Unusable 7 9 1 7 2 1 13 6 6 2 Total 234 7 51 6 62 0 403 0 182 0 Capacities Oil Engine oil tank 3...

Page 36: ...3 002 NOTES 1 HELICOPTER ON GROUND WITH FULL FUEL TYPICAL ATTITUDE OF CARGO DECK 4 7 DEGREES NOSE UP 2 IF OPTIONAL EXTENDED LANDING GEAR IS INSTALLED ADD 0 87 FEET TO ALL VERTICAL DIMENSIONS 3 ALL DIMENSIONS ARE IN FEET Figure 1 1 MD 500E Principal Dimensions Standard Landing Gear ...

Page 37: ...160 140 120 100 80 60 40 20 0 200 180 160 140 120 100 80 60 40 20 0 220 240 260 280 300 320 MPH Km Hr Knots F03 003 EXAMPLE CONVERT 100 KNOTS TO MPH AND TO KM HR ENTER CHART AT 100 KNOTS AND FOLLOW ARROW TO SLOPING LINE TO FIND MPH MOVE LEFT AND READ 115 MPH TO FIND KM HR MOVE RIGHT FROM THE SLOPING LINE AND READ 185 KM HR Figure 1 2 Speed MPH Knots KmH ...

Page 38: ...MPERATURE 50 F METHOD ENTER AT 50 F READ 10 C ACROSS ON C SCALE METHOD MAY BE REVERSED TO FIND F WHEN C IS KNOWN ALTERNATE METHOD F 9 5 X C 32 C 5 9 F 32 TEMPERATURE EXAMPLE F C 140 120 100 80 60 40 20 0 20 40 60 60 40 20 0 20 40 60 80 F03 004 50 30 10 10 30 50 Figure 1 3 Temperature Conversion Chart ...

Page 39: ... 340 69 344 47 348 26 352 05 355 83 359 62 363 40 367 19 370 97 374 76 100 378 54 382 33 386 11 389 90 393 69 397 47 401 26 405 04 408 83 412 61 110 416 40 420 18 423 97 427 75 431 54 435 62 439 11 442 89 446 68 450 46 Table 1 4 Linear Measure Inches to Centimeters 0 1 2 3 4 5 6 7 8 9 Inches Cm Cm Cm Cm Cm Cm Cm Cm Cm Cm 0 2 54 5 08 7 62 10 16 12 70 15 24 17 78 20 32 22 86 10 25 40 27 94 30 48 33 ...

Page 40: ...8 651 28 955 29 260 29 565 29 870 30 174 100 30 479 30 784 31 089 31 394 31 698 32 003 32 308 32 613 32 918 33 222 Table 1 6 Weight Pounds to Kilograms 0 1 2 3 4 5 6 7 8 9 Pounds Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams Kilo grams 0 0 454 0 907 1 361 1 814 2 268 2 722 3 175 3 629 4 082 10 4 536 4 990 5 443 5 897 6 350 6 804 7 257 7 711 8 16...

Page 41: ...CONVERT KNOTS TO METERS SEC KNOWN WIND SPEED 25 KT METHOD ENTER CHART AT 25 KT READ APPROXIMATELY 13 METERS SEC ACROSS ON METERS SEC SCALE METHOD MAY BE REVERSED TO FIND KNOTS WHEN METERS SEC ARE KNOWN EXAMPLE 0 5 10 15 20 25 30 35 40 45 50 0 5 10 15 20 25 Figure 1 4 Conversion Chart Knots Meters Second ...

Page 42: ... 2 29 1 29 0 28 9 28 7 28 6 28 5 28 4 28 3 28 2 28 1 28 0 28 8 1055 1050 1045 1040 1035 EXAMPLE 1 29 44 IN HG 997 MBAR EXAMPLE 2 30 18 IN HG 1022 MBAR 1035 1030 1025 1020 1015 1010 1005 1000 IN Hg 30 6 30 7 30 8 30 9 31 0 31 1 30 5 2 1 30 5 29 5 29 6 29 7 29 8 29 9 30 0 30 1 30 2 30 3 30 4 F03 006 Figure 1 5 Conversion Chart Inches of Mercury Millibars ...

Page 43: ...0 0 7860 1 1279 0 850 30 471 752 63 22 225 0 7428 9000 0 7620 1 1456 2 831 26 905 724 29 21 388 0 7148 10000 0 7385 1 1637 4 812 23 338 696 82 20 577 0 6877 11000 0 7155 1 1822 6 793 19 772 670 21 19 791 0 6614 12000 0 6932 1 2011 8 774 16 206 644 40 19 029 0 6360 13000 0 6713 1 2205 10 756 12 640 619 44 18 292 0 6113 14000 0 6500 1 2403 12 737 9 074 595 23 17 577 0 5875 15000 0 6292 1 2606 14 718...

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Page 45: ... Shaft N2 Limits 250 C20R 2 2 8 2 9 Electrical System Limitations 2 9 2 10 Starter Limitations 2 9 2 11 Fuel System Limitations 2 9 Table 2 1 Unusable Fuel Standard Non Self Sealing Fuel Tanks 2 10 Table 2 2 Unusable Fuel Optional Self Sealing Fuel Tanks 2 10 Figure 2 4 Operating Limitations when Using MIL G 5572E Emergency Fuel Aviation Gasoline 2 11 2 12 Instrumentation 2 12 Figure 2 5 Instrumen...

Page 46: ......

Page 47: ...e used for an additional pilot when the approved dual controls are installed Aerobatic flight is prohibited Hovering downwind with a cyclic trim failure full forward when wind is above 15 knots is prohibited Installed equipment Certification is based on an Engine Failure Warning System including both visual and audio indications Low Rotor Warning System Outside Air Tem perature gauge and Fuel Low ...

Page 48: ...om sea level to 6000 feet pressure altitude the maximum engine air inlet ambient temperature is 54 C 130 F from 6000 feet to 20 000 feet pressure altitude the maximum temperature varies linearly from 54 C to 27 C 130 F to 80 F respectively It is to be assumed that engine air inlet temperature is the same as ambient free air temperature Cold weather operations Flight into known icing conditions is ...

Page 49: ...ge 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 Figure 2 1 98 99 100 102 104 106 108 GROSS WEIGHT POUNDS 1600 107 4 1800 2000 2200 2400 2600 2800 3000 FUSELAGE STATION INCHES FORWARD AFT F03 007 MINIMUM FLYING WEIGHT 1538 POUNDS LATERAL CG LATERAL CG FORWARD AIRCRAFT CENTERLINE ...

Page 50: ...e starting The rotor brake may be applied after engine shutdown with the rotor at or be low 205 RPM 2 6 ROTOR RPM SPEED LIMITATIONS Normal Operating Range 487 RPM to 492 RPM 102 103 percent N2 Power on maximum RPM is 492 RPM Ref 103 percent N2 Power on minimum RPM is 487 RPM Ref 102 percent N2 Power off maximum RPM is 523 RPM Ref 109 percent N2 Power off minimum RPM is 410 RPM Ref 87 percent N2 ...

Page 51: ...g lightoff 150 C Maximum continuous 755 C with torque at or below 74 3 psi torque 738 C with torque greater than 74 3 psi torque Transient limits During start and shutdown 810 C and above for 10 seconds or less with a momentary peak temperature of 927 C for not more than 1 second During power changes in flight 810 C to 843 C for 6 seconds Gas producer N1 speed limits Maximum continuous 105 Minimum...

Page 52: ...102 103 104 105 106 107 108 110 111 112 113 TOT o C PERCENT SPEED OUTPUT SHAFT N2 100 99 109 NORMAL OPERATION POWER ON POWER ON ROTOR LIMIT 15 SECONDS POWER OFF ROTOR LIMIT REF F03 008 MAXIMUM Figure 2 2 Maximum Allowable Output Shaft N2 Limits 250 C20B Engine oil system limits Flight operation temperature limits 0 C to 107 C NOTE These engine oil temperature limits pertain to all gauge configurat...

Page 53: ...t limits During start and shutdown 810 C and above for 10 seconds or less with a momentary peak temperature of 927 C for not more than 1 second During power changes in flight 810 C to 843 C for 6 seconds for aircraft with analog only TOT indica tor 810 C to 899 C for 6 seconds for aircraft with analog digital TOT indi cator Gas Producer N1 speed limits Maximum continuous 105 Minimum ground idle sp...

Page 54: ...02 103 104 105 106 107 108 110 111 112 113 TOT o C PERCENT SPEED OUTPUT SHAFT N2 100 99 109 NORMAL OPERATION POWER ON POWER ON ROTOR LIMIT 15 SECONDS POWER OFF ROTOR LIMIT REF F03 008 MAXIMUM Figure 2 3 Maximum Allowable Output Shaft N2 Limits 250 C20R 2 Engine oil system limits Flight operation temperature limits 0 C to 107 C NOTE These engine oil temperature limits pertain to all gauge configura...

Page 55: ...STM D 1655 JP 1 conforming to ASTM D 1655 Jet A or Jet A 1 JP 4 MIL DTL 5624 JP 5 MIL DTL 5624 JP 8 MIL DTL 83133 Arctic Diesel Fuel DF A conforming to ASTM D 1655 Jet A or Jet A 1 Diesel No 1 conforming to ASTM D 1655 Jet A or Jet A 1 Peoples Republic of China RP 3 Alternate AVGAS JetA A 1 JP 5 or JP 8 mixture may be used at ambient tem peratures of 4 C and below Refer to Rolls Royce Operation an...

Page 56: ... anti ice additives above fuel temperatures of 30 F 34 C However the continued use of anti ice additives under all temperature conditions is recommended to provide addi tional protection against fuel system icing and microbiological contamina tion Fuel filter Upon completion of the flight in progress further flight is prohibited until the fuel filter has been serviced following the illumination of...

Page 58: ...URE C20B ANALOG TORQUEMETER C20R 2 87 2 PSI 81 3 TO 87 2 PSI 0 TO 81 3 PSI 810 C 752 TO 810 C 360 TO 752 C 843 C TURBINE OUTLET TEMPERATURE C20 R2 ANALOG DIGITAL ANALOG 400 TO 752 C 752 TO 810 C 810 C 899 C 927 C 150 C RED RED INDICATES MAXIMUM AND MINIMUM OPERATING LIMITS THE EDGE OF A RED LINE IS THE LIMITING VALUE THE POINTER SHOULD NOT ENTER THE RED DURING NORMAL OPERATIONS GREEN GREEN INDICAT...

Page 59: ...10 2A N2 RPM ROTOR RPM 410 AND 523 RPM 410 TO 523 RPM 102 AND 103 102 TO 103 113 DUAL TACHOMETER FACE SHOWN TWICE FOR CLARITY 35 POUNDS 12 5 POUNDS FUEL QUANTITY N1 TACHOMETER 59 AND 105 64 TO 105 152 KNOTS 42 TO 152 KNOTS MAX AUTOROTATION SPEED 130 KNOTS AIRSPEED Figure 2 5 Instruments Sheet 2 of 3 ...

Page 60: ... C 54 TO 107 C C 107 C 0 TO 107 C C ENGINE OIL TEMPERATURE LATER CONFIGURATION ENGINE OIL TEMPERATURE EARLIER CONFIGURATION OIL PRESS PSI 0 50 100 150 50 AND 130 PSI 50 TO 90 PSI 90 TO 130 PSI ENGINE OIL PRESSURE 150 75 0 85 D C AMPS 150 AMMETER 150 AMPS 85 TO 150 AMPS 0 TO 85 AMPS Figure 2 5 Instruments Sheet 3 of 3 ...

Page 61: ...06 45 150 143 122 103 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 85K MIN DO NOT EXCEED CHART VNE MAX VNE 130 KTS WITH LESS THAN 35 LB FUEL VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2001 TO 2500 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 127 122 118 113 104 90 20 149 144 139 134 129 124 113 96 84 10 151 145 140 135 123 104 90 0 146 138 113 97 85 10 152 124 105 91 20 143 115 98 86 30 127 107 93 NO...

Page 62: ...ED BY 22K 95K MIN DO NOT EXCEED CHART VNE MAX VNE 130 KTS WITH LESS THAN 35 LB FUEL Figure 2 6 VNE Placards Rolls Royce 250 C20B Sheet 2 of 2 250 C20R 2 VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2000 LB OR LESS C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 126 122 117 113 108 104 20 148 143 138 133 129 124 119 114 100 10 150 145 138 135 130 125 108 0 151 146 141 135 116 101 10 152 145 133 109 20 149...

Page 63: ...TOROTATION VNE REDUCE SPEED BY 21K 90K MIN DO NOT EXCEED CHART VNE MAX VNE 130 KTS WITH LESS THAN 35 LB FUEL 250 C20R 2 VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2501 TO 3000 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 126 122 111 94 80 68 20 148 143 138 133 122 101 86 74 62 10 150 145 140 110 93 80 68 0 151 122 102 87 74 63 10 152 141 111 94 81 69 20 124 103 88 76 64 30 144 113 96 82 71 NO FLI...

Page 64: ... WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL CAUTION CYCLIC FORCES TO BE TRIMMED TO NEUTRAL DURING STARTUP AND SHUTDOWN NOTE Above placards located on instrument panel 50 POUNDS MAXIMUM LOAD UNIFORMLY DISTRIBUTED NOTE Above placard located inside utility stowage compartment IF MOISTURE VISIBLE AND OAT BELOW 5 C USE ANTI ICE NOTE Above placard located by OAT ga...

Page 65: ...ater Landing 3 7 3 7 Fire 3 9 Engine Fire on the Ground 3 10 Engine Fire During Flight 3 11 Cabin Fire Smoke 3 12 3 8 Engine FUEL Control System Malfunctions 3 14 Fuel Control or Power Turbine governor Failure 3 14 3 9 Other Engine Caution Indications 3 16 Engine Chip Detector 3 16 Low Engine Oil Pressure 3 16 Engine Torque 3 16 3 10 Main Rotor and Tail rotor Transmission Malfunctions 3 17 M R Tra...

Page 66: ...3 22 3 13 Fuel System Malfunctions 3 22 Fuel Filter 3 22 Fuel Low 3 23 3 14 Electrical System Malfunctions 3 24 Battery Overtemperature 3 24 Generator Malfunction 3 25 3 15 Other Malfunctions 3 26 Engine Air Particle Separator Filter Clogged If installed 3 26 3 16 Emergency Egress 3 27 Figure 3 2 Emergency Exits 3 27 3 17 Emergency Equipment 3 27 ...

Page 67: ...ew passengers aircraft or personnel on the ground These procedures are recommended to minimize danger to the helicopter How ever these procedures should not limit the pilot from taking additional actions if the situation warrants In the event of an emergency or malfunction the pilot s primary consider ation is control of the aircraft Then the pilot must identify the problem and perform the appropr...

Page 68: ... 11 12 13 14 15 16 ENGINE OUT AUDIBLE WARNING HORN SEE NOTE CAUTION AND WARNING LIGHTS OPTIONAL EQUIPMENT NOTE ON LATER MODEL 369E HELICOPTERS ENGINE OUT AUDIBLE WARNING HORN RELOCATED ADJACENT TO COCKPIT UTILITY LIGHT ON MAP CASE PANEL F03 011 1 ENGINE OUT 2 TRANSMISSION OIL PRESSURE 3 TRANSMISSION OIL TEMPERATURE 4 BATTERY TEMPERATURE 160 F 5 BATTERY TEMPERATURE 140 F 6 RE IGN PRESS TO RESET 7 F...

Page 69: ...indicators are actuated when N1 falls below 55 or NR falls below 468 NR Ref 98 1 N2 Procedures Engine Failure In Cruise at 500 Feet AGL or Above Adjust collective pitch according to altitude and airspeed to maintain rotor speed between 410 and 523 RPM Apply pedal pressure as necessary to control aircraft yaw Adjust cyclic control as necessary to control airspeed and flight path Al low airspeed to ...

Page 70: ...mplete loss of power time and altitude permitting place twistgrip in cutoff and close fuel shutoff valve Select landing area and maneuver as required If operating at reduced rotor RPM to extend glide or reduce rate of de scent restore rotor RPM by lowering collective prior to flare out Flare as required for the terrain to reduce forward speed and rate of de scent Level aircraft before ground conta...

Page 71: ...round at which the power loss occurs As the ground is approached flare as required to reduce forward speed and rate of descent Touch down in a level attitude increasing collective pitch to cushion land ing Avoid the use of aft cyclic or rapid lowering of the collective during initial ground contact or during ground slide Procedures Engine Failure Hovering Flight Below 12 Feet AGL Do not reduce col...

Page 72: ...ocedures Close twist grip to cutoff position Press start ignition button immediately NOTE Pressing the starter button actuates the igniter If N1 is 18 percent or above open twist grip immediately to ground idle N1 speeds of 25 to 40 percent are preferred for coolest and fastest restarts Maintain safe autorotational airspeed Conditions When altitude and time permit Procedures Perform normal engine ...

Page 73: ...id increases in power Governor failure producing an underspeed Procedures Respond immediately to the low rotor RPM warning by adjusting collec tive to maintain rotor RPM within limits Check other Caution Warning indicators and engine instruments to con firm engine trouble and respond in accordance with appropriate proce dures in this section 3 6 EMERGENCY LANDING PROCEDURES WATER LANDING Condition...

Page 74: ...tions Power on Procedures Descend to hovering altitude over water Open doors and push door handle full down to prevent relatching Passengers and copilot exit aircraft Fly a safe distance away from all personnel in the water to avoid injury Close twistgrip to the cutoff position and perform a hovering autorotation Allow aircraft to settle in a level attitude while applying full collective pitch Whe...

Page 75: ... sound of electrical arcing the smell of burning insulation or the sighting of smoke and or flame are all possible indicators of an on board fire Also the pilot may be notified of an on board fire by personnel outside the aircraft via visual or audio communication methods At unprepared landing sites dried grass or brush may catch fire if allowed to contact hot engine exhaust Procedures Cabin Smoke...

Page 76: ...eans to extinguish and control the fire have been tried The pilot s first responsibility is to fly the helicopter and land immediately Once on the ground with passengers and crew evacuated attention can be turned to extinguishing the fire If a fire extinguisher is discharged in the cabin use only the amount of extinguishing agent necessary to extinguish the fire This will minimize the adverse effe...

Page 77: ...ew EVACUATE IF TIME AND SITUATION PERMIT Rotor brake if installed APPLY Secure area HAVE PASSENGERS AND SPECTATORS MOVE A SAFE DISTANCE FROM THE AIR CRAFT Fire extinguisher USE AS APPROPRIATE ENGINE FIRE DURING FLIGHT Conditions At low altitude AGL Procedures Land immediately POWER ON APPROACH AND LANDING WITHOUT DELAY Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND Fuel shutoff valve PULL TO ...

Page 78: ...f autorotational descent to the ground If a power off descent is chosen proceed as follows Collective DOWN TO ESTABLISH AUTOROTATION TO SELECTED AREA Twistgrip CUTOFF Fuel shutoff valve PULL TO CLOSE Radio MAYDAY CALL Execute autorotational landing MAINTAIN CONTROL BAT EXT switch OFF Passengers crew EVACUATE CABIN FIRE SMOKE Conditions On ground Procedures Twistgrip CUTOFF BAT EXT switch OFF Passe...

Page 79: ...BIN AS NECESSARY Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND BAT EXT switch OFF Passengers crew EVACUATE IF UNABLE TO LAND IMMEDIATELY AND FIRE SOURCE CAN BE IDENTIFIED Malfunctioning system OFF Fire extinguisher USE AS NECESSARY Cabin VENTILATE Land AS SOON AS POSSIBLE IF FIRE SOURCE IS UNKNOWN Cabin heat OFF Generator OFF All electrical circuits not required for safety of flight OFF Cabi...

Page 80: ...increasing Possible right yaw Procedures Increase collective to load the main rotor simultaneously rolling the twist grip toward the ground idle position until control of N2 speed is obtained Manually control N2 speed 102 103 with the pilots twistgrip If operating RPM cannot be controlled close twistgrip to CUTOFF and make an autorotational landing Immediate pilot action is necessary because engin...

Page 81: ...light or a power on decent make an au torotational landing Conditions Power Turbine Governor Surge Indications N2 fluctuating governor not maintaining pre set speed 102 103 N2 Procedures NOTE Turning the start pump ON may allow the engine to operate smoothly If operation of the engine returns to normal it may be possible to fly to a favorable landing area however do not disregard the need to land ...

Page 82: ...oon as possible LOW ENGINE OIL PRESSURE Indications Oil pressure decreasing below normal operating range Ref Section II Conditions In flight Procedures Land as soon as possible Shut engine down Conditions On ground Shut engine down ENGINE TORQUE Indications Loss of engine torque indication NOTE Loss of torque indication may be the result of broken torque meter tubing Conditions In flight Procedure...

Page 83: ...d as soon as possible M R TRANSMISSION OIL TEMPERATURE Indications Red XMSN OIL TEMP indicator ON Conditions Transmission oil temperature exceeds maximum limit Procedures Land as soon as possible M R TRANSMISSION CHIP DETECTOR Indications Yellow M R XMSN CHIPS indicator ON Conditions Metal contamination of oil Procedures Land as soon as possible TAIL ROTOR TRANSMISSION CHIP DETECTOR Indications Ye...

Page 84: ...ower setting Indications Failure is normally indicated by an uncontrollable by pedal yawing to the right Procedures Reduce power by lowering collective Adjust airspeed between 50 to 60 knots Use left lateral cyclic in combination with collective pitch to limit left sideslip to a reasonable angle If conditions permit place the twistgrip in the ground idle position once a landing area is selected an...

Page 85: ...ck forces in the longitudinal cyclic control system Indications Aft feedback in the cyclic at high airspeed and or during pull ups from high airspeed or higher than normal forces required to move the cyclic longitudinally NOTE If the one way lock has a push rod shaft or check valve seizure in the closed valve position a pull or push of 10 to 20 pounds will be necessary to open the hydraulic relief...

Page 86: ... continued flight Indications Inoperative trim Conditions The trim motor fails to respond to application of the cyclic trim switch in one or more directions Procedures Establish a safe flight condition that produces the least cyclic control force Normally straight and level at the last trimmed airspeed Actuate the trim switch thru all positions in an attempt to restore trim capability and determin...

Page 87: ... longitudinal runaway trim failure is experienced it may be possible to reduce cyclic stick forces by maintaining higher airspeeds Cyclic stick forces may be reduced if an aft longitudinal runaway trim failure is experienced by maintaining slower airspeeds Lateral runaway trim forces cannot be reduced by adjusting flight conditions Utilize left hand and legs as necessary to apply pressure against ...

Page 88: ... cause of the vibration has been identified and corrected 3 13 FUEL SYSTEM MALFUNCTIONS FUEL FILTER Indications Yellow FUEL FILTER indicator ON Conditions A predetermined pressure differential across the filter has been reached and an impending bypass condition exists Procedures Turn on start pump Continue flight If any unusual engine indications or conditions occur land as soon as possible Servic...

Page 89: ...f fuel quantity Procedures Avoid large steady side slip angles and uncoordinated maneuvers Sideslips may cause fuel starvation and result in unexpected power loss or engine failure Avoid large steady side slip angles uncoordinated maneuvers or speeds above 130 knots IAS when FUEL LEVEL LOW caution indicator is illuminated Land as soon as possible Fuel consumption rates vary with power demand Pilot...

Page 90: ...temp relay removes the battery from the DC electrical bus when battery temperature reaches 160 F Land as soon as possible NOTE No further flights are authorized until battery is inspected and cause of overtemp corrected Indications Yellow BAT TEMP 140 indicator ON Conditions Battery overtemperature at 140 F 60 C Procedures Battery switch OFF Battery must remain off line during remainder of flight ...

Page 91: ... not powering electrical bus Procedures Check generator GEN circuit breaker IN and return generator switch to ON if tripped OFF 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 NOTE The generator switch must be in the ON position to en...

Page 92: ...e yellow caution indicator to flicker momentarily The FILTER BYPASS DOOR should be opened only when a steady illumination of the caution indicator is five seconds or more Conditions A predetermined pressure differential has been reached across the engine air inlet Procedures FILTER BYPASS control handle OPEN SCAV AIR OFF Service particle separator prior to next flight Ref HMI To prevent compressor...

Page 93: ... COMPARTMENT DOOR EXIT TO OPEN TO LOCK EXIT PILOT COMPARTMENT DOOR LH TYPICAL F03 012 Figure 3 2 Emergency Exits 3 17 EMERGENCY EQUIPMENT First Aid Kit The first aid kit is located on the right side forward edge of the pilot s seat structure The kit is a commercial type containing the items necessary to render lim ited emergency first aid Fire Extinguisher The fire extinguisher is located on the p...

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Page 95: ...nt Panel RH Command Layout Typical 4 10 Figure 4 4 Cyclic and Collective Stick Grips 4 11 4 2 Engine Pre Start Cockpit Check 4 12 4 3 Engine Start 4 15 4 4 Engine Run Up 4 17 4 5 Before Takeoff 4 20 4 6 Takeoff 4 22 4 7 Cruise 4 23 4 8 Low Speed Maneuvering 4 23 4 9 Practice Autorotation 4 24 4 10 Doors Off Flight 4 25 4 11 Landing Approach 4 25 4 12 Running Landing 4 25 4 13 Engine Aircraft Shutd...

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Page 97: ...ence of corro sion These are the most common types of damage however checks should not be limited to these items Further checks shall be performed before the next flight if discrepancies are noted to determine if the aircraft is airworthy Flight is prohibited when unrep aired damage exists which makes the aircraft unairworthy Have a thorough understanding of operating limitations Ref Section II Se...

Page 98: ...Normal Procedures CSP E 1 ROTORCRAFT FLIGHT MANUAL MD 500E Model 369E Revision 13 4 2 FAA Approved F03 013 Figure 4 1 Pilot s Preflight Guide ...

Page 99: ...valve unless start pump is ON An unexpected flameout or power loss may occur if air is allowed to enter the fuel system EXTERIOR FUSELAGE FORWARD END Aircraft tiedowns and covers REMOVED Aircraft attitude for weak or damaged landing gear dampers CHECK Canopy for condition and cleanliness CHECK OAT thermometer sun shield CHECK Fresh air vent NO OBSTRUCTIONS Pitot tube NO OBSTRUCTIONS Tail rotor ped...

Page 100: ...otor hub pitch control rods blade dampers swashplate and mast CHECK Main rotor blades for chordwise cracks on the underside of the blade skin and doubler If existing the cracks will be at the leading and trailing edges of the root fitting in the area of the two most outboard bolts or outermost end of lower root fitting CHECK Oil cooler air inlet NO OBSTRUCTIONS Engine air inlet plenum chamber NO O...

Page 101: ...or axial play between the conical bearing inner and outer races No play is allowed CHECK Tail rotor drive fork elastomeric bearings if installed NOTE Check bearing for general condition Elastomeric bearings are suspected of being unserviceable if rubber deterioration or separation or a vibration is noted Evidence of light swelling pock marks and crumbs are surface conditions and are not indication...

Page 102: ...ondition and bonding do not handle trim tabs CHECK Overrunning clutch turn main rotor blade forward then aft CHECK All inspection panels SECURED ENGINE COMPARTMENT Engine mounts mounting pads and firewalls CHECK Landing gear attach points rear dampers leaks and inflation CHECK Engine oil air and fuel lines CHECK Scavenge oil filter bypass indicator if installed CHECK Fuel filter bypass indicator C...

Page 103: ...l access doors SECURED Controls access door SECURED Loose equipment or cargo SECURED Seats seat belts and shoulder harness CHECK Compartment doors closed and latched CHECK NOTE Refer to Paragraph 4 10 if planning doors off flight FORWARD COMPARTMENT Battery compartment CHECK Fire extinguisher and first aid kit CHECK Loose equipment or cargo CHECK NOTE Refer to Paragraph 4 10 if planning doors off ...

Page 104: ...or to subsequent flights of the same day Fluid levels CHECK Engine compartment fluid leaks and bypass indicators CHECK Air inlet screens particle separator CHECK Fuel cap access doors and panels CHECK Main rotor blades CHECK Tailboom and empennage CHECK Tail rotor rotor blades CHECK Cargo and loose equipment CHECK Crew and cabin doors CHECK ...

Page 105: ...CATOR FRESH AIR VENT FUEL SHUTOFF VALVE QUANTITY INDICATOR EDGE LIGHTED SWITCH PANEL PRE AND LATE GENERIC EARLY GENERIC F03 014 1 DUAL TACHOMETER ANTI ICE SWITCH 250 C20R 2 ENGINE OUT AUDIBLE WARNING HORN SEE NOTE NOTE ON LATER MODEL 369E HELICOPTERS ENGINE OUT AUDIBLE WARNING HORN RELOCATED ADJACENT TO PILOT S UTILITY LIGHT ON MAP CASE PANEL FUEL VALVE PULL FOR AIR TEMPERATURE TOT INDICATOR EDGE ...

Page 106: ...TURE INDICATOR ENGINE OIL PRESSURE INDICATOR FUEL TURBINE OUTLET AMMETER CLOCK N1 TACHOMETER TORQUE INDICATOR FRESH AIR VENT FUEL SHUTOFF VALVE QUANTITY INDICATOR EDGE LIGHTED SWITCH PANEL F03 014 2 DUAL TACHOMETER ANTI ICE SWITCH 250 C20R 2 FUEL VALVE PULL FOR AIR TEMPERATURE TOT INDICATOR EDGE LIGHTED CIRCUIT BREAKER PANEL Figure 4 3 Instrument Panel RH Command Layout Typical ...

Page 107: ...K FRICTION NUT TWIST GRIP LANDING LIGHT SWITCH GOVERNOR INCREASE DECREASE SWITCH COPILOT S SWITCH HOUSING CARGO HOOK CYCLIC TRIM DWN R L UP RELEASE OPTION COPILOT S COLLECTIVE OPTIONAL ICS COMM TRIGGER PILOT S COLLECTIVE STICK START BUTTON PILOT S COLLECTIVE SWITCH GOVERNOR INCREASE DECREASE SWITCH FLOAT INFLATE TWIST GRIP SWITCH OPTION F03 015 Figure 4 4 Cyclic and Collective Stick Grips ...

Page 108: ...s over center of body Operation of shoulder harness inertia lock CHECK Cyclic collective friction off and pedals FULL TRAVEL Cyclic stick NEUTRAL FRICTION ON NOTE Cyclic stick longitudinal neutral position is about 35 percent 1 3 travel from full aft lateral position may be determined by centering the friction control knob in the guide link Tail rotor pedals CENTERED Collective stick FULL DOWN FRI...

Page 109: ...h 500 amp load Maximum capacity 28 5V dc with 500 amp load Lights AS REQUIRED Key switch ON Engine Out Warning System Auto Reignition System Checks Pre Generic and Late Generic Configurations NOTE See Section I and Figure 4 2 to determine which version of the electrical system is installed in the aircraft GEN switch ON then OFF to check audible engine out warnings both external horn in the cabin a...

Page 110: ...n test switch to OFF Fuel gauge CHECK READING All other instruments CHECK XMSN OIL PRESS ENG OUT and GEN warning caution lights ON Press to test caution and warning lights CHECK Caution light dim switch CHECK NOTE BAT 140 and RE IGN P RST caution lights do not dim All other caution lights will return to bright when power is removed and restored by cycling the BAT switch or pulling and resetting th...

Page 111: ...c Configuration Only Start pump AS REQUIRED NOTE Start pump required when using alternate or emergency fuel Ref to Section II Rotors CLEARED Start ignition button PRESS AND HOLD NOTE Starter time limits are 1 minute ON 1 minute OFF 1 minute ON and 23 minutes OFF Rotate twistgrip to ground idle for ignition when N1 indicates 12 to 15 percent see Section II Minimum N1 Speed Starting Recommendations ...

Page 112: ...or at least ten seconds or until TOT decreases below 150 C Start ignition button release at 58 to 60 percent N1 RELEASE Engine oil pressure 50 to 130 psi CHECK NOTE During cold weather operation 150 psi oil pressure is allowable following an engine start Remain at ground idle RPM until normal oil pressure limits are attained All caution and warning indicators out CHECK NOTE Transmission oil pressu...

Page 113: ...TE Checks with an asterisk need only be performed prior to the first flight of the day Insure that an Auto Reignition Check is performed prior to flying into falling or blowing snow Electrical power SELECT BAT EXT switch SELECT BAT External power start DISCONNECT GPU Set generator GEN to ON GEN OUT caution light out ammeter will show charge OPERATE AND CHECK NOTE Monitor N1 and TOT when turning ge...

Page 114: ...for 1 minute before increasing power ENGINE CONTROLS ENGINE OUT AND LOW ROTOR WARNING AUTO REIGNITION CHECKS NOTE Whenever there is transmission oil pressure the auto reignition system is armed Press reignition RE IGN P RST light LAMP OUT N2 high beep range 104 to 105 CHECK N2 low beep range 98 or less CHECK Low rotor warning on at 98 1 CHECK NOTE ENGINE OUT light only no audio horn early generic ...

Page 115: ...e air system may be checked by verifying that the flapper door scavenge air outlet is open THROTTLE RIGGING CHECK NOTE If the flight will involve rolling the twistgrip to the ground idle position while airborne Autorotation training maintenance test flight etc this check must be performed even thought it may not be the first flight of the day N2 102 RECHECK Pilot s twistgrip SNAP TO IDLE If engine...

Page 116: ... heat ON Ref Sections V and VIII Collective control friction RELEASE AND SET AS DESIRED When removing collective friction be alert for abnormal collective loads that would cause the collective to raise by itself Cyclic response check With collective pitch full down gently move cyclic stick and observe rotor tip for correct movement and track CHECK All instruments in the green CHECK Position and an...

Page 117: ... 4 2 to determine which version early generic late generic of the generic wire harness is installed in the aircraft This check may be performed at the pilot s discretion Prior to takeoff While on the ground at 102 103 N2 place RE IGN test switch in the FLT middle position RE IGN and ENGINE OUT lights should illuminate Bring the aircraft to a hover and observe actuation of the engine out audible wa...

Page 118: ...mmended takeoff profile shown in Height Velocity Diagram Ref Section V If sudden unusual or excessive vibrations should occur during flight a precautionary landing should be made No further flights shall be attempted until the cause of the vibration has been identified and corrected NOTE Momentary fluctuation in indicated airspeed may occur during acceleration and climbout This fluctuation is char...

Page 119: ...ld be avoided NOTE Conditions where thrust limits may be approached are High density altitude high gross weight rapid pedal turns and placing the helicopter in a down wind condition These conditions may exceed the thrust capability of the tail rotor Extreme aircraft attitudes and maneuvers at low speeds should be avoided Uncoordinated turns maneuvers may cause fuel starvation with less than 35 pou...

Page 120: ...nt rotor overspeed if flight is at high gross weight or high density altitude To re duce rate of descent or to extend gliding distance operate at minimum rotor rpm Restore ROTOR RPM NR by lowering collective prior to flareout If a power recovery is desired lower collective to full down rotate the twistgrip to the full open position verify that N2 is between 102 and 103 percent and that full engine...

Page 121: ... RPM 4 10 DOORS OFF FLIGHT Doors off flight is permitted in accordance with the restrictions noted in Sec tion II Any object that is not properly secured may exit the aircraft during flight Items secured with Velcro i e first aid kit seat cushions should not be considered properly secured Secure or stow in the baggage compartment all loose equipment Secure or remove unoccupied seat cushions Use ea...

Page 122: ...stick neutral position approximately 1 3 from full aft TRIM TO NEUTRAL APPLY FRICTION All unnecessary bleed air and electrical equipment OFF Pedals maintain until rotor has stopped CENTERED Twistgrip from GROUND IDLE to CUTOFF position SET NOTE Immediately after closing twistgrip to the CUTOFF position a dual tachometer needle split should occur with NR lagging behind N2 If no needle split occurs ...

Page 123: ...harness is installed in the aircraft Auto reignition light ON Do not use collective pitch to slow rotor Generator switch OFF NAV COM switches OFF All other switches OFF Rotor brake if installed apply at 205 rpm or less release during last rotor revolution APPLY Care should be taken when applying the rotor brake if the helicopter is parked on slippery or icy surface The tail rotor has little effect...

Page 124: ...N Stabilize N2 at exactly 103 percent BEEP as required for 15 seconds SET Pilot s twistgrip SNAP TO IDLE Begin time check with stop watch Stop time as N1 passes through 65 per cent Observe elapsed time Minimum allowable lapsed time is 2 seconds NOTE Practice or retakes may be required before proficiency can be obtained in deceleration timing If deceleration time is less than two seconds make two m...

Page 125: ...mperative that every pilot subject the public to the least possible noise while flying the helicopter Takeoff Takeoff using maximum takeoff power at the speed for best rate of climb Ref Section V Proceed away from noise sensitive areas If takeoff must be made over noise sensitive area distance altitude is best form of noise suppression Cruise Maintain 1000 feet minimum altitude where possible Main...

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Page 127: ...r 4 Bladed Tail Rotor Rolls Royce 250 C20B 5 11 Figure 5 7 Hover Ceiling VS Gross Weight IGE 3 5 Foot Skid Clearance Standard or Extended Landing Gear 4 Bladed Tail Rotor Rolls Royce 250 C20B 5 12 Figure 5 8 Hover Ceiling VS Gross Weight IGE 3 5 Foot Skid Clearance Utility Floats Installed Rolls Royce 250 C20B 5 13 Figure 5 9 Hover Ceiling VS Gross Weight IGE 5 Foot Skid Clearance Utility Floats I...

Page 128: ...50 C20R 2 5 19 5 6 Height Velocity Diagram Gross Weight Limits For Height Velocity Diagram 5 20 Figure 5 15 Height Velocity Diagram 5 21 Figure 5 16 Gross Weight Limits for Height Velocity Diagram 5 22 5 7 Power Check Rolls Royce 250 C20B Engine 5 23 Figure 5 17 Power Check Chart Rolls Royce 250 C20B Engine 5 25 5 8 Power Check Rolls Royce 250 C20R 2 5 27 Figure 5 18 Power Check Chart Rolls Royce ...

Page 129: ...able Data is applicable to the basic helicopter without any optional equipment installed unless otherwise noted NOTE Unless otherwise stated the performance data put forth in this section applies to MD 500E Model 369E Helicopters equipped with either the Rolls Royce 250 C20B or 250 C20R 2 engines Select the appropriate power check and hover performance charts for type of engine installed See Engin...

Page 130: ...to known pressure altitude line move to left and note densi ty altitude NOTE Pressure altitude is found by setting 29 92 1013 mb in kolsman window altimeter error To determine true airspeed convert indicated airspeed IAS to calibrated airspeed CAS utilizing the Airspeed Calibration Curve Figure 5 2 Read value on right of chart opposite known density altitude Multiply CAS by this value to determine...

Page 131: ... 20 30 40 2000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 DENSITY ALTITUDE FEET 0 98 1 00 1 02 1 04 1 06 1 08 1 10 1 12 1 14 1 16 1 18 1 20 1 22 1 24 1 26 1 28 1 30 1 32 1 34 1 36 TEMPERATURE C TEMPERATURE F 50 60 40 30 20 10 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 Figure 5 1 Density Altitude Chart ...

Page 132: ...rror equals calibrated airspeed CAS Use of Chart To determine calibrated airspeed the pilot must know the indicated air speed Example WANTED Calibrated airspeed KNOWN Indicated airspeed 120 knots METHOD Enter the bottom of the chart at the indicated airspeed of 120 knots Move up to the airspeed calibration line move left and read 120 5 knots calibrated airspeed By entering the chart from the oppos...

Page 133: ...NUAL MD 500E Model 369E Revision 14 5 5 FAA Approved F03 018 INDICATED AIRSPEED KNOTS CORRECTED FOR INSTRUMENT ERROR CALIBRATED AIRSPEED KNOTS 180 160 140 120 100 80 60 40 20 0 20 40 60 80 100 120 140 160 180 Figure 5 2 Airspeed Calibration Curve ...

Page 134: ...dicated 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 METHOD Enter the left side of chart at the known density altitude of 5000 feet Move to the right along line and read 62 KIAS as the speed for best rate of climb ...

Page 135: ...MANUAL MD 500E Model 369E Revision 14 5 7 FAA Approved F03 013 16000 14000 12000 10000 8000 6000 4000 2000 0 0 20 40 60 80 100 INDICATED AIRSPEED KNOTS CORRECTED FOR INSTRUMENT ERROR DENSITY ALTITUDE FEET Figure 5 3 Speed for Best Rate of Climb ...

Page 136: ...trated to be adequate in winds up to 17 knots Use of Chart The following example explains the correct use of the chart in Figure 5 4 To determine the maximum gross weight for hovering at 3 5 ft skid height the pilot must know the pressure altitude and the outside air temperature Example WANTED Maximum gross weight for hover at 3 5 feet skid height at takeoff power KNOWN PA 8000 feet OAT 25 C METHO...

Page 137: ...N HEAT ENGINE ANTI ICE OFF ELECTRICAL LOAD 10 AMPERE APPLICABLE TO PARTICLE SEPARATOR SCAVENGE OFF OR STANDARD ENGINE AIR INLET REDUCE WEIGHT 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY F03 017 1 ROLLS ROYCE 250 C20B DECREASE WEIGHT REDUCE WEIGHT CAPABILITIES lb...

Page 138: ...ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 DWT 1 2 3 NOT VERIFIED WHEN MAIN ROTOR BLADES HAVING ABRASION STRIPS ARE INSTALLED REDUCE WEIGHT CAPABILITIES lbs ...

Page 139: ... OR STANDARD ENGINE AIR INLET REDUCE WEIGHT 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 DWT 1 2 3 NOT VERIFIED WHEN M...

Page 140: ...3600 INCREASE WEIGHT 50 LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50 LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY NOT VERIFIED WHEN MAIN ROTOR BLADES HAVING ABRASION STRIPS ARE INSTALLED INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 DWT 1 2 3 REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS APP...

Page 141: ...HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 220 152 111 86 232 157 117 89 469 306 227 172 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 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WE...

Page 142: ... HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 220 152 111 86 232 157 117 89 469 306 227 172 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 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE W...

Page 143: ... ICE OFF ELECTRICAL LOAD 10 AMPERE APPLICABLE TO PARTICLE SEPARATOR SCAVENGE OFF OR STANDARD ENGINE AIR INLET REDUCE WEIGHT 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDU...

Page 144: ... ABRASION STRIPS ARE INSTALLED 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 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY INCRE...

Page 145: ...15 35 DWT 1 2 3 NOT VERIFIED WHEN MAIN ROTOR BLADES HAVING ABRASION STRIPS ARE INSTALLED 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 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 50LB WITH ABRAS...

Page 146: ... ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50 LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY ISA ISA 20 OAT C NOT VERIFIED WHEN MAIN ROTOR BLADES HAVING ABRASION STRIPS ARE INSTALLED NOTE SKID CLEARANCE 4 5 FEET FOR STANDARD LANDING GEAR INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 DWT 1 2 3 REDUCE WEIGHT CAPABI...

Page 147: ...BRASION STRIPS ON TAIL ROTOR BLADES ONLY F03 037 3 INCREASE OR DECREASE WT CAPABILITY LBS ABOVE CRITICAL ALTITUDE PER 10 AMP REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 DWT 1 2 3 NOT VERIFIED WHEN MAIN ROTOR BLADES HAVING ABRASION STRIPS ARE INSTALLED REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS APPLICABLE TO ALL TEMPERATURES PRESSURE ALT FT CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 1...

Page 148: ...cross hatched area is not prohibited but should be avoided The recommended takeoff profile line shows the airspeed altitude combina tions recommended for takeoff The unmarked region represents the area in which safe autorotational land ings may be performed with average pilot skill and reaction time Gross Weight Limits for Height Velocity Diagram Ref Figure 5 16 Description The gross weight limits...

Page 150: ...ance Data MD 500E Model 369E Revision 14 5 22 FAA Approved F03 016 2 GROSS WEIGHT POUNDS DENSITY ALTITUDE FEET 7000 6000 5000 4000 3000 2000 1000 0 2000 2200 2400 2600 2800 3000 3200 Figure 5 16 Gross Weight Limits for Height Velocity Diagram ...

Page 151: ...tion on trend analysis The power check chart is based on the following conditions 103 percent N2 Cabin heat and engine anti ice OFF Particle separator SCAV AIR OFF 10 amperes electrical load Engine bleed valve closed Use Of Chart The primary use of the chart is illustrated by the example below and by the sample arrows shown on the chart To determine power check values it is necessary to read and r...

Page 152: ...er than the specification TOT read from the chart some power deterioration will have occurred and the performance data given in this manual may not be obtained 3 When trend check procedures indicate engine power deterioration re fer to the Rolls Royce Operation and Maintenance Manual for corrective action NOTE Data obtained during engine engine operation with the bleed valve not fully closed will ...

Page 153: ... PSI SHAFT HORSEPOWER MODIFIED 250 C20B ENGINE POWER CHECK CHART WITH BLANKED OUT AREA FOR ENGINE OPERATION WITH BLEED VALVE OPEN TOT LIMIT 810 C TURBINE OUTLET TEMPERATURE DEGREES CELSIUS DEGREES FAHRENHEIT 1000 1200 1300 1400 1500 1100 10 C 14 F 0 C 30 F 10 C 50 F 20 C 68 F 40 C 104 F 50 C 122 F 30 C 86 F MAX TORQUE PRESSURE ALTITUDE TO READ POWER REFLECT OFF SEA LEVEL LINE N2 103 CABIN HEAT ANT...

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Page 155: ...20B Power Check Chart First an adjustment to the OAT should be made before entering the chart add 2 5 C if the data was taken in a hover or 1 C if the data was taken in forward flight The second change is the addition of Accel eration Bleed Valve Open lines to the chart any reflection of data that falls below the appropriate dashed altitude reference line should be disregarded as it may involve a ...

Page 156: ...th the TOT observed during flight 650 C for this example The TOT that was observed is higher than the specification TOT However note that the junction of the 10 C curve with the 645 C TOT line lies below the 8000 foot PA bleed line dashed line Thus it is an inappropriate region in to which to determine power The higher than spec TOT is probably due to the accelerating bleed valve being partially o...

Page 157: ...00 TOT LIMIT 810 C F03 021 2 TURBINE OUTLET TEMPERATURE DEGREES CELSIUS ACCELERATING BLEED VALVE OPEN AVOID ENGINE CHECK IN REGION BELOW APPROPRIATE ALTITUDE LINE 25 30 35 40 45 50 55 60 70 75 65 80 85 TO READ POWER REFLECT OFF SEA LEVEL LINE CABIN HEAT ANTI ICE OFF SCAVENGE BLEED OFF ELECTRICAL LOAD 10 AMPS TORQUE LIMIT 87 2 PSI TORQUE PSI SHAFT HORSEPOWER 200 250 300 350 400 Figure 5 18 Power Ch...

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Page 159: ...rt Sheet 2 of 2 6 8 Figure 6 5 Sample Surplus and Missing Items 6 9 Figure 6 6 Sample Weight and Balance Record 6 10 6 4 Weight and Balance Determination Passenger Configuration 6 11 6 5 Longitudinal Loading of Cargo 6 13 6 6 Permissible Lateral Loadings 6 15 6 7 Lateral Loading of Cargo 6 15 Figure 6 7 Fuel Station Diagram Jet A at 6 8 Pounds per Gallon Sheet 1 of 2 6 17 Figure 6 7 Fuel Station D...

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Page 161: ...ation 100 Cargo Deck Capacity 1300 pounds not to exceed 115 pounds per square foot Utility Stowage Compartment Limited to 50 pounds Center of Gravity Limits Lateral is right of centerline lateral is left of centerline when look ing forward Table 6 1 Center of Gravity Limits Gross Weight Longitudinal C G Limit Sta in Lateral C G Limit Sta in lb Forward Aft Right Left 3000 99 0 103 0 3 0 2500 99 0 1...

Page 162: ...e Data MD 500E Model 369E Revision 14 6 2 98 99 100 102 104 106 108 110 GROSS WEIGHT POUNDS 1538 1600 107 4 1800 2000 2200 2400 2600 2800 3000 96 LONGITUDINAL ARM INCHES MINIMUM FLYING WEIGHT F03 019 97 Figure 6 1 Longitudinal Center of Gravity Limits ...

Page 163: ... 0 STA 73 5 STA 100 0 STA 78 5 CG OF COPILOT CG OF PILOT CARGO COMPARTMENT STA 124 0 ROTOR C L 0 0 12 2 12 2 STA 105 0 174 0 REFERENCE DATUM STA STA 15 0 15 5 13 0 STA 73 5 STA 100 0 STA 78 5 CG OF PILOT CG OF RIGHT CARGO COMPARTMENT STA 124 0 ROTOR C L 12 2 12 2 STA 105 0 0 8 174 0 PASSENGER STA 71 5 CG OF FWD PASSENGER SIDE FWD TW0 PLACE COCKPIT LEFT HAND COMMAND THREE PLACE COCKPIT WITH SINGLE ...

Page 164: ... CG LIMITS SLING POINT OIL TANK RH SIDE LEVELING PLUMB STA 92 6 FIRE WALL JIG POINT AFT JACKING STA 174 0 BHD POINT STA 197 2 STA 284 0 107 4 REFERENCE DATUM BATTERY STA 78 5 JIG POINT FWD JACKING POINT STA 96 9 BL 25 6 WL 11 98 STA 124 0 FUEL CELL COMPARTMENT ENGINE SECTION 3 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 Figure 6 2 Reference Coordinates Sheet 2 of 2 ...

Page 165: ...CSP E 1 Weight and Balance Data ROTORCRAFT FLIGHT MANUAL MD 500E Model 369E Revision 14 6 5 F03 021 Figure 6 3 Station Diagram ...

Page 166: ...ered weight includes oil and unusable fuel 6 3 EQUIPMENT REMOVAL OR INSTALLATION Removal or addition of equipment must be entered on the repair and alteration report form FAA 337 in accordance with Federal Air Regulations which shall then become part of the helicopter log book file Record the weight and balance effects of these changes in the Weight And Bal ance Record inserted in this section Use...

Page 167: ...0 0 721 7 96 9 69933 RIGHT MAIN 591 7 0 0 591 7 96 9 57915 TAIL 182 0 0 0 182 0 197 2 35890 TOTAL UNADJUSTED NET WEIGHT 1495 4 109 1 163138 TOTAL WEIGHT OF SURPLUS EQUIPMENT SEE TABLE 1 1 3 96 9 126 TOTAL WEIGHT OF MISSING EQUIPMENT SEE TABLE 1 15 9 97 4 1549 TOTAL BASIC WEIGHT 1510 0 109 0 164561 REFER TO THE OWNER S MANUAL FOR C G LIMITS APPLICABLE FOR GROSS WEIGHT RANGE FUEL OIL AT TIME OF WEIG...

Page 168: ...ROSS WEIGHT 99 0 INCHES EXAMPLE 2 AFT WEIGHT LBS LONG ARM IN LONG MOMENT IN LB BASIC WEIGHT 1510 0 109 0 164561 PILOT 170 0 73 5 12495 PASSENGER AFT L H 170 0 105 0 17850 PASSENGER AFT R H 170 0 105 0 17850 BAGGAGE UNDER AFT SEAT 50 0 110 0 5500 GROSS WEIGHT ZERO FUEL AFT C G 2070 0 105 4 218256 APPROVED AFT C G LIMIT FOR EXAMPLE 2 GROSS WEIGHT 105 8 INCHES EXAMPLE 3 LATERAL WEIGHT LBS LATRL ARM I...

Page 169: ...tion No Date WEIGHT ARM INCHES MOMENT IN LBS EQUIPMENT ITEM LBS LONG LATR LONG LATR SURPLUS EQUIPMENT TOTAL 1 3 96 9 0 126 0 JACK PADS 2 1 3 96 9 0 126 0 MISSING EQUIPMENT TOTAL 15 9 97 4 0 0 1549 0 ONE QT ENGINE OIL 2 1 133 1 0 0 280 0 UNUSABLE FUEL 12 0 93 0 0 0 1116 0 FLIGHT MANUAL 1 8 85 0 0 0 155 0 Page 3 of 4 Figure 6 5 Sample Surplus and Missing Items ...

Page 170: ... BASIC WEIGHT AND BALANCE RECORD CONTINUOUS HISTORY OF CHANGES IN STRUCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE SERIAL NUMBER REGISTRATION NUMBER WEIGHT CHANGE ADDED REMOVED RUNNING TOTAL BASIC AIRCRAFT WEIGHT ARM LONG MOMENT WEIGHT ARM Hughes Helicopters Inc PAGE 4 OF 4 IN LB LONG MOMENT IN LB WEIGHT ARM LONG MOMENT IN LB F03 022 1510 0 109 0 164561 Figure 6 6 Sample Weight and Balance Reco...

Page 171: ...ding center of gravity for gross weight by dividing total moment by gross weight This computation must be done with zero fuel gross weight and with mission fuel gross weight see Example I NOTE If loadings are not symmetrical about the aircraft centerline determine lateral CG s as described in Paragraphs 6 6 and 6 7 Weight and balance must be computed for minimum front seat weight prior to loading ...

Page 172: ...850 Passenger Aft L H 170 17 850 Utility Stowage Station 52 9 20 1058 Baggage under seat Station 110 0 40 4 400 1 Zero Fuel Weight Add Useable Fuel 62 1 GAL Jet a 6 8 LB GAL 2 250 422 230 709 41 229 2 Gross Weight 2 672 271 938 Calculation of Longitudinal CG CG Zero Fuel Weight Moment at Zero Fuel Weight 230 709 Zero Fuel Weight 2 250 102 5 IN CG Gross Weight Moment at Gross Weight 271 938 Gross W...

Page 173: ...will be within the approved CG limits To determine the gross weight and center of gravity for a given flight are with in limits proceed as follows Establish the weight of the cargo load Determine the location of the cargo longitudinal CG by measuring the dis tance to the cargo from the jacking point located on the side of the fuselage station 96 9 Cargo CG 96 9 measured distance inches ie if aft o...

Page 174: ...assenger Fwd Outboard 170 12 495 Cargo Station 100 0 1000 100 000 1 Zero Fuel Weight Add Usable Fuel 22 0 GAL Jet a 6 8 LB GAL 2 850 150 289 551 14 175 2 Gross Weight 3 000 303 726 Calculation of Longitudinal CG CG Zero Fuel Weight Moment at Zero Fuel Weight 289 551 Zero Fuel Weight 2 850 101 6 IN CG Gross Weight Moment at Gross Weight 303 756 Gross Weight 3 000 101 2 IN NOTE The CG falls within t...

Page 175: ...rnal loadings are permissible if gross weight longitudinal and lateral center of gravity considerations permit For crew and passenger lateral center of gravity see Figure 6 2 6 7 LATERAL LOADING OF CARGO To determine if the gross weight and lateral center of gravity for a given flight are within limits Proceed as follows Find weight of load Determine lateral location station of load center of grav...

Page 176: ...t L H 170 13 0 2 210 Passenger Fwd R H 170 15 5 2 635 Cargo 1000 2 0 2 000 1 Zero Fuel Weight 2 850 0 9 2 425 Add Usable Fuel 22 0 GAL Jet a 6 8 LB GAL 150 0 0 2 Gross Weight 3 000 0 8 2 425 Calculation of Lateral CG CG Zero Fuel Weight Moment at Zero Fuel Weight 2 425 Zero Fuel Weight 2 850 0 9 IN CG Zero Fuel Weight Moment at Gross Weight 2 425 Gross Weight 3 000 0 8 IN NOTE The CG falls within ...

Page 177: ...ITY IS 422 POUNDS OPTIIONAL SELF SEALING TANKS 1 MAXIMUM FUEL QUANTITY IS 420 5 POUNDS 2 MAXIMUM USABLE FUEL QUANTITY IS 407 5 POUNDS FUEL WT AND CG CURVE USING JET A LONGITUDINAL C G INCHES FUEL QUANTITY GALLONS 65 60 55 50 45 40 35 30 25 20 15 10 5 0 ASTM D 1655 AT 6 8 POUNDS PER GALLON EXAMPLE Find fuel moment for 340 lb fuel 1 Enter chart at 340 lb on fuel weight scale From that point move to ...

Page 178: ... IS 403 5 POUNDS OPTIIONAL SELF SEALING TANKS 1 MAXIMUM FUEL QUANTITY IS 402 POUNDS 2 MAXIMUM USABLE FUEL QUANTITY IS 389 5 POUNDS FUEL WT AND CG CURVE USING JET B LONGITUDINAL C G INCHES FUEL QUANTITY GALLONS 65 60 55 50 45 40 35 30 25 20 15 10 5 0 EXAMPLE Find fuel moment for 340 lb fuel 1 Enter chart at 340 lb on fuel weight scale From that point move to right along the 340 lb line until reachi...

Page 179: ...0 11 760 11 440 16 800 170 12 495 12 155 17 850 180 13 230 12 870 18 900 200 14 700 14 300 21 000 220 16 170 15 730 23 100 240 17 640 17 160 25 200 Baggage Weights and Longitudinal Moments Baggage Moment in lb Moment in lb Moment in lb Moment in lb Weight lb Utility Stowage Compartment Station 52 9 Fwd Bulkhead Station 87 Under Seat and Center Station 110 Behind Seat Station 120 10 529 870 1 100 1...

Page 180: ... L H Station 13 0 Passenger R H Fwd Station 15 5 Passenger Center Fwd Station 0 8 Aft Passenger R H and L H Station 12 2 120 1 560 1 860 96 1 464 140 1 820 2 170 112 1 708 160 2 080 2 480 128 1 952 170 2 210 2 635 136 2 074 180 2 340 2 790 144 2 196 200 2 600 3 100 160 2 440 220 2 860 3 410 176 2 684 240 3 120 3 720 192 2 928 BAGGAGE WEIGHTS AND MOMENTS Baggage Weight lb Station 12 8 Moment in lb ...

Page 181: ...ERAL Aft Compartment Passenger Weights and Longitudinal Moments High Density Seating Table 6 4 Weight and Loading for 369H90035 503 Seating and Belts for Four Installation High Density Seating Passenger s lb Moment In lb Fwd position Sta 95 5 Moment in lb Aft Position Sta 109 2 150 14 300 16 400 175 16 700 19 100 200 19 100 21 800 225 21 500 24 600 250 23 900 27 300 275 26 300 30 000 300 28 700 32...

Page 182: ...pical tiedown for 500 pound cargo Restraint loops are to be secured as indicated and tied to the cargo to pre vent slippage of the loops Variations of the tiedown are allowable providing total restraint require ments are met Caution should be exercised to keep the cargo from bearing against the cen ter slanted portion of the aft bulkhead Table 6 5 Cargo Weight Versus Loop Restraint Number of Requi...

Page 183: ...VIEW I LOOP FOR VERTICALAND LATERAL RESTRAINT VIEW SHOWING LOCATION OF CARGO TIEDOWN POINTS AND LOOPS MINIMUM LOOP STRINGTH 1800 LB WRAP CONTAINER WITH SIMILAR STRAP SUCH THAT LOOPS CANNOT SLIP VIEW II CARGO CARGO FLOOR VIEW SHOWING 500 LB CARGO RESTRAINED A CARGO FLOOR F03 025 Figure 6 8 Cargo Restraint ...

Page 184: ......

Page 185: ...Servicing Materials Operating Supplies 7 7 Figure 7 4 Servicing Points Sheet 1 of 2 7 11 Figure 7 4 Servicing Points Sheet 2 of 2 7 12 7 8 Fuel System Servicing 7 13 7 9 Engine Oil System Servicing 7 14 7 10 Main Rotor and Tail Rotor Transmission Servicing 7 14 7 11 Cleaning General 7 15 7 12 Cleaning Fuselage Interior Trim and Upholstery 7 15 7 13 Cleaning Aircraft Exterior and Rotor Blades 7 16 ...

Page 186: ......

Page 187: ...th sufficient amperage rating may be used Engine starting requirements are approximately 375 amperes mini mum Before connecting external power be sure that helicopter main electrical power selector switch is OFF After power is connected to receptacle power switch must be set to EXT posi tion to connect external power to helicopter electrical system 7 3 HOISTING JACKING AND LIFTING Hoisting lifting...

Page 188: ...NSTALLATION FORWARD SECTION INSTALLATION PILOT DOOR ASSEMBLY HORIZONTAL STABILIZER VERTICAL STABILIZER TAILBOOM AFT SECTION INSTALLATION TAIL ROTOR TRANSMISSION TAIL ROTOR ASSEMBLY ENGINE INSTALLATION MAIN TRANSMISSION AND POWER TRAIN ENGINE ACCESS DOOR CARGO DOOR LOWER SECTION INSTALLATION LANDING GEAR F30 026 Figure 7 1 MD 369E Helicopter Major Components ...

Page 189: ...helicopter by hand and for towing helicopter Ref Figure 7 2 At regular intervals check that wheel tire pressure is a maximum of 80 to 90 psi F03 029 WARNING BE SURE LOCK SNAPS INTO POSITION SHOWN BEFORE RELEASING JACK HANDLE LOCK TOW BAR FITTING JACK HANDLE WHEELS LOWERED AND LOCKED HELICOPTER RAISED GROUND HANDLING WHEELS AND JACK ASSEMBLY HANDLE LOCK PIN SKID TUBE RIGHT SIDE SHOWN SKID FITTING W...

Page 190: ...s raising helicopter Manually move helicopter on ground handling wheels by balancing at tail boom and pushing on rear fuselage portion of air frame Towing Tow helicopter on ground handling wheels by attaching suitable tow bar to tow bar fittings If tow bar is not equipped to keep front ends of skid tubes from dragging have an assistant balance helicopter at tailboom Ensure all stress panels are in...

Page 191: ...ntil one blade is directly above tailboom Ref Figure 7 3 Install blade socks on all blades Secure blade sock tiedown cord for blade located above tailboom to tailboom Secure other blade sock tiedown cords to fuselage jack fittings or cabin steps When securing blade sock tiedown cords take up slack but do not apply excessive bending loads on blades Mooring Ref Figure 7 3 Whenever severe storm condi...

Page 192: ...RD ZIPPER ENGINE AIR INLET FAIRING COVER INSTALLATION JACK FITTING INSTALLATION TYPICAL 2 PLACES TO MOORING ANCHOR TO BLADE SOCK JACK FITTING LOCKPIN PITOT TUBE COVER INSTALLATION PITOT TUBE COVER FUEL CELL ACCESS DOOR LOCKPIN STOWAGE FUESELAGE AIR INLET FAIRING F05 042 TIEDOWN TETHER ENGINE EXHAUST COVER LATCH COVER STRUCTURE JACK FITTING F03 030 Figure 7 3 Parking and Mooring ...

Page 193: ...67 liters Use the materials listed under Item 4 or Mobil SHC 626 3 Main Transmission 369F5100 Capacity 14 0 US Pt 6 62 liters Use Mobil SHC 626 only 4 Engine Capacity 3 0 US Qt 2 84 liters Ambient Temperature Oil Type 0 C 32 F and above MIL PRF 23699C or subsequent preferred 0 C 32 F to 40 C 40 F MIL PRF 23699C or subsequent preferred or MIL PRF 7808G or subsequent 40 C 40 F and below MIL PRF 7808...

Page 194: ...ast Hanover NJ 07936 Hatcol 3211 Hatco Corporation King George Post Road Fords New Jersey 08863 BP Turbo Oil 2380 EXXON Turbo Oil 2380 Air BP Castrol Aero Jet5 Castrol Industrial North Amer ica Specialty Products Division 5511 District Blvd Los Angeles CA 90040 Hatco Corporation MIL PRF 23699F Series Mobil Jet 254 and Mobil Jet 291 ExxonMobil Lubricants Aeroshell Royco Turbine Oil 560 Royal Lubric...

Page 195: ...STM D 1655 Jet A or Jet A 1 MIL DTL 83133 grade JP 8 CAUTION At 4 4 C 40 F and below fuel must contain anti icing additive that meets MIL I 27686 requirements For blending information and authorized fuels refer to the appropriate Rolls Royce Operation and Maintenance Manual 6 Overrunning Clutch 369A5350 Capacity 1 64 US Oz 45cc Use the materials listed under item 4 but not Mobil SHC 626 7 Overrunn...

Page 196: ...r Gear Value in excess of 2500 pounds per inch 2 Not a preferred lubricant for transmissions Use MIL PRF 7808 lubricating oil in transmission only when other oils are not available 3 For Model 250 Series engine oil change requirements and restrictions on mixing of oils refer to Rolls Royce Operation and Maintenance Manual DO NOT use Mobil SHC 626 oil in 250 Series engines WARNING Only discretionar...

Page 197: ...TEM FILLER ENGNE OIL TANK FILLER FUEL CELL DRAIN VALVE ENGINE ACCESSORY GEARBOX DRAIN LIQUID LEVEL SIGHT GAGE OVERBOARD OIL DRAIN LINE ENGINE COMBUSTION FUEL DRAIN GROUND RECEPTACLE LIQUID LEVEL SIGHT GAGE BREATHER FILLER MAIN TRANSMISSION DRAIN VALVES TAIL ROTOR TRANSMISSION DRAIN TRANSMISSION OIL LEVEL SIGHT GAUGE OIL FILTER BYPASS INDICATOR 369F5100 M R TRANSMISSION ONLY Figure 7 4 Servicing Po...

Page 198: ...ion 14 7 12 FAA Approved ENGINE OIL TANK DRAIN ENGINE OIL COOLER DRAIN STATION 137 50 BULKHEAD MAIN TRANSMISSION OIL COOLER DRAIN ENGINE WASH FITTING SCAVENGE OIL FILTER BYPASS INDICATOR ENGINE FUEL FILTER BYPASS INDICATOR 250 C20 R2 SP ENGINE F03 031 2 Figure 7 4 Servicing Points Sheet 2 of 2 ...

Page 199: ...3A or later type fuels contain anti ice additive which conforms to MIL 1 27686 or later These fuels do not require additional anti ice additive Cold weather fuel mixtures To assure consistent starts at temperatures at or below 4 C 40 F a mixture of AVGAS and jet fuels other than JP 4 or Jet B may be used The alternate avgas jet fuel mixture is not recommended for warm weather operation Refer to Al...

Page 200: ...oil in the engine oil system Make certain that oil tank filler cap is secured after servicing 7 10 MAIN ROTOR AND TAIL ROTOR TRANSMISSION SERVICING Main rotor transmission Check transmission oil level at liquid level sight gauge Ref Figure 7 4 NOTE Indicated oil level may be incorrect if aircraft is not level or has been ground handled in a tail low attitude since last flight Replenish with correc...

Page 201: ...ive action and or leave residue that can result in corrosion Examples of cleaning agents that are not to be used are Fantastic and 409 type cleaners or locally made strong soap cleaners 7 12 CLEANING FUSELAGE INTERIOR TRIM AND UPHOLSTERY Clean dirt or dust accumulations from floors and other metal surfaces with vacuum cleaner or small hand brush Sponge soiled upholstery and trim panels with a mild...

Page 202: ...urfaces of plastic by rinsing with clean water and rubbing light ly with palm of hand Use mild soap and water solution or aircraft type plastic cleaner to remove oil spots and similar residue Never attempt to dry plastic panels with cloth To do so causes any abrasive particles lying on plastic to scratch or dull surface Wiping with dry cloth also builds up an electrostatic charge that attracts dus...

Page 203: ...uation of damper in service can cause inter nal damage that might not otherwise occur NOTE It is normal for a thin hydraulic oil film to remain on damper piston as a result of wiping contact with piston seal Newly installed dampers may also have slight oil seepage from oil trapped in end cap threads during damper assembly Neither of these should be considered damper leakage or cause from damper re...

Page 204: ...xt flight Remove covers and equipment used to park and moor helicopter Perform daily preflight check Ref Section IV 7 18 COCKPIT DOOR REMOVAL AND INSTALLATION Door removal Open door Remove interior cover plates pilot s side remove fire extinguisher Pull lower hinge pin up to remove While holding door rotate upper hinge pin until hinge pin tab clears the slot and pull down on pin to remove Remove d...

Page 205: ...FLIGHT MANUAL MD 500E Model 369E Revision 14 7 19 FAA Approved DOOR FRAME PILOT S DOOR DOOR STRUCTURE DOOR HINGE FUSELAGE STRUCTURE HINGE PIN TAB F60 043 PASSENGER CARGO COMPARTMENT DOOR LH SHOWN RH SIMILAR Figure 7 5 Pilot and Passenger Cargo Door Removal ...

Page 206: ...aning process The starter generator can be used to motor the Allison 250 Series en gine for compressor cleaning cycle Input voltage should be 24 vdc but it is permissible to use 12 vdc To prevent starter generator damage duty cycle cranking time limits that must not be exceeded are 24 vdc External Auxiliary Power 24 vdc Helicopter Battery Power 25 Seconds ON 30 Seconds ON 30 Seconds OFF 2 Minutes ...

Page 207: ...hree seconds prior to starter engagement Motor the engine with the twistgrip in CUTOFF Release starter switch as necessary to maintain between 5 and 10 N1 speed during the wash rinse Water injection will continue during coast down until N1 stops Allow engine to drain Within 15 minutes of the water rinse operate the engine at idle for five minutes and actuate anti ice cabin heat and scav air if ins...

Page 208: ......

Page 209: ...Out of Ground Effect OGE 8 1 Figure 8 1 Hover Ceiling Versus Gross Weight Out of Ground Effect Takeoff Power Two or Four Bladed Tail Rotor Rolls Royce 250 C20B 8 2 Figure 8 2 Hover Ceiling Versus Gross Weight Out of Ground Effect Takeoff Power Two or Four Bladed Tail Rotor Rolls Royce 250 C20R 2 8 3 Figure 8 3 Hover Ceiling Versus Gross Weight Out of Ground Effect Utility Floats Installed Takeoff ...

Page 210: ......

Page 211: ...de air temperature or alternately the maximum hover ceiling for a known gross weight and outside air temperature The hover ceiling vs gross weight charts are based on 1 Takeoff power at 103 N2 2 Cabin heat and engine anti ice OFF 3 Electrical load of 10 amps 4 Wind less than 3 knots Use of chart To determine OGE hover performance refer to Section V Hover Ceiling IGE Use of chart NOTE Aircraft with...

Page 212: ...THAN 3 KNOTS CABIN HEAT ENGINE ANTI ICE OFF ELECTRICAL LOAD 10 AMPERE APPLICABLE TO PARTICAL SEPARATOR SCAVENGE OFF OR STANDARD ENGINE AIR INLET 16000 14000 12000 10000 8000 6000 4000 2000 0 PRESSURE ALTITUDE FEET GROSS WEIGHT POUNDS 2200 2400 2600 2800 3000 3200 3400 3600 REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS APPLICABLE TO ALL TEMPERATURES PRESSURE ALT FT CABIN HEAT ANTI ICE BOTH SL TO 4000 8...

Page 213: ...TH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY DECREASE WEIGHT 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY AMPERE APPLICABLE TO REDUCE WEIGHT CAPABILITIES lbs AS FOLLOWS APPLICABLE TO ALL TEMPERATURES PRESSURE ALT FT CABIN HEAT ANTI ICE BOTH SL TO 4000 8000 12000 16000 289 256 176 129 396 316 217 157 639 557 381 278 ...

Page 214: ...HIS 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 1 55LB WITH SCAVENGE ON 2 40LB WITH MIST ELIMINATOR INSTALLED INCREASE WEIGHT 50LB WITH ABRASION STRIPS ON MAIN ROTOR BLADES ONLY 50LB WITH ABRASION STRIPS ON TAIL ROTOR BLADES ONLY MAXIMUM INTERNAL GROSS WEIGHT GROSS WEIGHTS ABOVE 300...

Page 215: ...9 3 Cargo Hook 9 10 9 6 Operating Instructions Anti Ice Airframe Fuel Filter 9 13 Figure 9 4 Anti Ice Airframe Fuel Filter 9 16 9 7 Operating Instructions Four Bladed Tail Rotor 9 17 Table 9 4 Center of Gravity Limits 9 21 Figure 9 5 Longitudinal Center of Gravity Limits 9 22 Figure 9 6 Lateral Center of Gravity Limits 9 23 9 8 Operating Instructions Emergency Floats 9 25 Figure 9 7 VNE Placards R...

Page 216: ...pment MD 500E Model 369E Revision 14 9 ii FAA Approved PARAGRAPH PAGE Figure 9 11 VNE Placards Sheet 2 of 2 9 43 Figure 9 12 Height Velocity Diagram Utility Floats Installed 9 46 Figure 9 13 Airspeed Calibration Curve Utility Floats Installed 9 47 ...

Page 217: ... to include a review of the appropriate flight manual supplemental data for type of optional equipment installed including STC items as a regular part of preflight planning 9 2 LISTING OPTIONAL EQUIPMENT Table 9 1 lists MDH optional equipment items available that require additional operating instructions This table does not include non MDHI STC items that may be FAA approved for use Other optional...

Page 218: ...on IX Emergency floats CSP E 1 Section IX Four bladed T R CSP E 1 Section IX Indicates data incorporated into the flight manual Sections I thru VII where appropriate NOTE See Table 9 2 for Optional Equipment Supplements certified for model 369E helicopters equipped with Allison Model 250 C20B engines only Table 9 2 Optional Equipment Model 369E Helicopter 250 C20B Equipment Publication No Anti ice...

Page 219: ... A 290121 B 290007 C 292500 D 90022 E 90148 F 90072 G 290086 H 292044 I 292044 A Emergency Floats 369D290121 527 X 1 2 X B Extended Landing Gear 369D290007 501 50 3 509 511 C Four Bladed Tail Rotor 369D292500 X X D Anti Ice Airframe Fuel Filter 369H90022 503 X E Engine Air Particle Separator Kit 369H90148 519 521 535 537 539 F Cargo Hook 369H90072 505 1 2 G Utility Floats 3 369D290086 501 503 X X ...

Page 220: ......

Page 221: ... 2000 pounds When the kit is installed an owner or operator holding a valid Rotorcraft Ex ternal Load Operator Certificate may utilize the helicopter for transportation of external cargo when operated by a qualified pilot OPERATIONS WITH CAR GO ON THE HOOK SHALL BE CONDUCTED IN ACCORDANCE WITH AP PLICABLE PORTIONS OF FEDERAL AVIATION REGULATIONS PART 133 Information provided in these operating ins...

Page 222: ...nds center of gravity limits for 3000 pounds apply Cargo Hook Limitations Cargo hook structural load limit is 2000 pounds Airspeed Limitations With no load on hook airspeed limits are unchanged With load on hook airspeed limits are presented on the exterior load VNE placards The airspeed presented on these placards apply to either C20B or C20R 2 engine installations NOTE Use caution as size and sh...

Page 223: ...ng External Load Limit 2000 Pounds installed on or next to cargo hook EXTERIOR LOAD VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 3200 LB OR LESS C 0 2 4 6 8 10 12 14 16 18 30 75 20 65 10 75 0 66 10 80 77 20 68 30 79 NO FLIGHT 40 45 EXTERIOR LOAD VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 3201 TO 3550 LB C 0 2 4 6 8 10 12 14 16 18 30 72 59 20 79 65 10 72 59 0 79 66 10 80 73 59 20 66 30 74 61 NO FLI...

Page 224: ...nical release handle to release cargo in the event of an elec trical failure Operate handle quickly and deliberately Ref Figure 9 2 NOTE Ground support personnel should manually assure positive reset of the cargo hook after use of mechanical release prior to further cargo pickups Static electricity discharge Instruct ground crew to insure that the helicopter has been electrically grounded prior to...

Page 225: ...ctrical and emergency operation of cargo hook release Ref Figure 9 3 Check operation of external release knob located on left side of cargo hook body Hook should return to the closed position after above checks Move pilot s cyclic to all extreme positions Cargo hook must remain locked and external release knob must not rotate With load ring in cargo hook swing hook to the limits of trav el in all ...

Page 226: ... 10 FAA Approved EXTERNAL RELEASE TURN CLOCKWISE ELECTRICAL WIRE HARNESS KEEPER MANUAL RELEASE CABLE HOOK LOAD BEAM 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 227: ...Loading Data should be used by the opera tor to assist in evaluating the helicopter center of gravity for various hook load weights Cargo Hook Loading Data Cargo Longitudinal CG 99 3 Cargo Weight lb Moment 100 in lb 100 99 200 199 300 298 400 397 500 497 600 596 700 695 800 794 900 894 1000 993 1100 1092 1200 1191 1300 1291 1400 1390 1500 1490 1600 1589 1700 1688 1800 1787 1900 1887 2000 1986 ...

Page 228: ......

Page 229: ...lete the requirement for use of fuel containing anti ice additives The anti ice airframe fuel filter incorporates a filter unit mounted in series between the aircraft fuel system and the engine fuel system Electrical and mechanical equipment sense the build up of ice in the filter unit and will automatically illuminate a cockpit caution on the annunciator panel The pi lot then actuates a switch to...

Page 230: ...t to exceed limitations of Basic RFM Section II Anti Ice fuel additives Installation of the Anti Ice Airframe Fuel Filter eliminates the need for anti ice fuel additives in the fuel i e Prist Placards Anti Ice Airframe Fuel Filter Installation For ground temp of 5 C or less max ALT 12 000 HP For ground temp greater than 5 C max ALT 14 000 HP PART III EMERGENCY AND MALFUNCTION PROCEDURES ANTI ICE A...

Page 231: ... on the bottom of the filter unit NOTE If aircraft has been exposed to freezing temperatures failure to drain may be due to ice formation in the filter element Start Pump OFF Press red press to test button located on the top of filter unit Ref Figure 9 4 AIR FRAME FILTER light should come on Release press to test button AIR FRAME FILTER light should go out Post flight filter cleaning When ambient ...

Page 232: ...RCRAFT FLIGHT MANUAL Optional Equipment Anti Ice Airframe Fuel FIlter MD 500E Model 369E Revision 14 9 16 FAA Approved FILTER BOWL FIREWALL TEST BUTTON ANTI ICE DRAIN VALVE Figure 9 4 Anti Ice Airframe Fuel Filter ...

Page 233: ...er It consists of two principal assemblies a four bladed tail rotor and gearbox The pedal bungee has been changed to compensate for tail rotor produced loads There is a weight increase of 9 4 pounds which will cause an aft C G shift of 0 6 to 0 9 inch depending on gross weight The exact shift must be determined by individual helicopter weight and balance The four bladed tail rotor turns at reduced...

Page 234: ...with the optional equipment depicted in Section IX Table 9 3 Rotor speed limits Minimum RPM Power Off 415 NR lower red bar on rotor tachometer Center of gravity envelope The forward CG limit is 99 0 inches the aft CG varies linearly from 103 0 inches at 3000 pounds gross weight to 106 0 at 2000 pounds then linearly to 108 1 at minimum flying weight of 1592 pounds Ref Table 9 4 The lateral CG limit...

Page 235: ...escent is obtained at 60 knots and 415NR PART IV NORMAL PROCEDURES Preflight check Output shaft dust cover retaining nut tang washer and rubber bumper CHECK Deformation of the teetering stop support portion of the retaining nut may indicate that excessive T R flapping has occurred and should be inspected in accordance with the HMI prior to flight Engine start Pedals NEUTRAL Excessive tail rotor fl...

Page 236: ... of the stop support may lead to the shearing of the inner key on the tang washer and subsequent loosening of the retaining nut Practice autorotation Practice autorotation should be conducted at 130 knots IAS or below see VNE placards Maintain rotor speed between 415 and 523 RPM by use of collective control Maximum gliding distance is obtained at 80 knots 415NR Minimum rate of descent is obtained ...

Page 237: ... Longitudinal C G Limit Sta in Lateral C G Limit Sta in Forward Aft Right Left 3000 99 0 103 0 3 0 2500 99 0 104 5 3 0 2300 99 0 105 1 3 0 2000 99 0 106 0 3 0 1592 99 0 108 1 1 7 The forward CG limit is 99 0 inches the aft CG varies linearly from 103 0 inches at 3000 pounds gross weight to 106 0 at 2000 pounds then linearly to 108 1 at minimum flying weight of 1592 pounds The lateral CG limits are...

Page 238: ...ed Tail Rotor MD 500E Model 369E Revision 14 9 22 FAA Approved F03 042 LONGITUDINAL ARM INCHES GROSS WEIGHT POUNDS 108 1 3000 2800 2600 2400 2200 1800 1600 2000 98 99 100 101 102 103 104 105 106 107 108 109 1592 LB Figure 9 5 Longitudinal Center of Gravity Limits ...

Page 239: ...Model 369E Revision 14 9 23 FAA Approved F03 043 3000 2800 2600 2400 2200 2000 1800 1600 LATERAL ARM INCHES GROSS WEIGHT POUNDS 1500 1592 5 4 3 2 1 0 1 2 3 4 5 1 7 1 7 AIRCRAFT CENTERLINE RIGHT LATERAL CG LIMIT LEFT LATERAL CG LIMIT FORWARD Figure 9 6 Lateral Center of Gravity Limits ...

Page 240: ...n 14 9 24 FAA Approved 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 241: ... circuits for each float This indi cator is located on the caution and warning indicator panel The circuit break er is located at the bottom of the circuit breaker panel A recessed switch is provided on the cyclic stick for the pilot to initiate inflation when required The switch activates valves allowing air or nitrogen stored in pressure vessels within the float packages to inflate the floats An...

Page 242: ...erating temperature range Operational temperature range for over water flight is 25 F 31 7 C minimum 117 F 47 C maximum Altitude limits floats inflated For water and ground landings change of altitude is limited to 6500 feet below the altitude at inflation or to 6500 feet below the maximum alti tude to which the inflated floats are subsequently flown This assumes the normal variation in ambient te...

Page 243: ...0 Placards When emergency floats are installed the following placards are required Placard 1 Placard 2 WARNING FLOAT INFLATION ABOVE 81 KNOTS IAS AT LESS THAN 6 000 FEET ALTITUDE 77 KNOTS IAS AT 6 000 FEET AND ABOVE IS PROHIBITED NIGHT FLIGHT OVER WATER BEYOND AUTOROTATION CAPABILITY TO GROUND IS PROHIBITED NOTE Placard 2 not required if 369D292032 Night Landing Kit is installed VNE Placards Refer...

Page 244: ...PEED BY 22K 85K MIN DO NOT EXCEED CHART VNE FLOATS STOWED VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 1680 TO 2000 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 127 122 118 113 109 104 20 149 144 139 134 129 124 119 115 101 10 151 145 140 135 130 125 110 0 146 141 136 121 102 10 152 151 148 144 138 111 20 150 146 143 123 104 30 151 148 145 141 114 NO FLIGHT 40 150 147 143 126 106 45 149 146 143 121...

Page 245: ...7 115 98 86 45 149 135 111 95 83 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 90K MIN DO NOT EXCEED CHART VNE MAX VNE 130 KTS WITH LESS THAN 30 LB FUEL FLOATS STOWED VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2501 TO 3000 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 127 122 114 97 83 20 149 144 139 134 124 104 90 77 10 151 145 138 114 97 83 0 124 105 90 78 10 152 139 114 98 84 72 20 125 106 92 79 30 ...

Page 246: ...ED BY 22K 90K MIN DO NOT EXCEED CHART VNE 250 C20R 2 FLOATS STOWED VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 1680 TO 2000 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 126 122 117 113 108 104 20 148 143 138 133 129 124 119 114 99 10 150 145 140 135 130 125 108 0 151 146 141 135 118 100 10 152 150 147 144 132 109 20 149 145 142 120 102 30 154 147 144 138 111 NO FLIGHT 40 149 146 143 122 104 45 148...

Page 247: ...45 148 124 104 89 77 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 90K MIN DO NOT EXCEED CHART VNE MAX VNE 130 KTS WITH LESS THAN 30 LB FUEL 250 C20R 2 FLOATS STOWED VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2501 TO 3000 LB C 0 2 4 6 8 10 12 14 16 18 30 141 136 131 126 122 110 91 77 66 20 148 143 138 133 121 99 84 71 63 10 150 145 136 109 91 77 66 0 151 121 100 84 71 63 10 152 136 110 92 78 67 20 122...

Page 248: ... at 2 000 feet or less above landing sur face to minimize differential pressure change with altitude change For over water operation in conditions near the Height Velocity Diagram immediate pilot reaction will be required to ensure float inflation prior to water contact Make a normal landing approach Minimize forward speed prior to water contact Recommended water contact speed 10 knots or less Do ...

Page 249: ...attery EXT when using an external power source Check FLOATS circuit breaker IN Press to test green float FLOAT P TEST LH RH indicator LH and RH indicator lamps should illuminate indicating that each circuit is operational Landing Tail low landings on hard surfaces should be avoided as stress damage to the float extensions may occur In flight float inflation data Float inflation time and altitude r...

Page 250: ...HAND SKID LEFT HAND SIMILAR Figure 9 9 Float Pressure Gauge 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 251: ...ects into the engine air inlet which might be of sufficient mass to puncture the inlet screen particle separator and damage the engine It reduces ingestion of large dust and sand particles It also reduces ingestion of snow and slush which may accumulate on the canopy at very slow speeds to be subse quently swept toward the inlet when forward speed is increased The kit in cludes a hub and engine ai...

Page 252: ... autorotation Ref Figure 9 10 Kit Compatibility The Mist Eliminator 369D290125 21 may not be used with the Engine Air Inlet Diverter Kit The Inlet Diverter Kit is not approved for use with the Allison 250 C20R 2 engine Placards Refer to Figure 9 10 for VNE limitations VNE IAS KTS INLET DIVERTER OAT PRESS ALT X 1000 GROSS WT 2000 LB OR LESS C 0 2 4 6 8 10 12 14 16 18 30 117 112 109 104 99 96 20 119...

Page 253: ...03 87 75 10 114 95 81 0 122 95 88 76 10 115 20 30 NO FLIGHT 40 45 FOR AUTOROTATION VNE REDUCE SPEED BY 23K 90K MIN DO NOT EXCEED CHART VNE VNE IAS KTS INLET DIVERTER OAT PRESS ALT X 1000 GROSS WT 2501 TO 3000 LB C 0 2 4 6 8 10 12 14 16 18 30 117 113 106 91 76 63 20 116 97 84 70 58 10 122 106 90 76 64 0 116 97 84 70 59 10 106 91 20 118 30 NO FLIGHT 40 45 FOR AUTOROTATION VNE REDUCE SPEED BY 23K 95K...

Page 254: ... 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 If at high cruise speed engine oil temperature approaches its limit it may be reduced by reducing airspeed ...

Page 255: ...id tube extensions two sets of stabilizing surfaces and the necessary hardware for attachment The floats mount on Extended Landing Gear An optional Night Landing Lighting Kit is available consisting of dual belly mounted sealed beam lights a circuit breaker and a three position switch installed on the collective control Forward position illuminates the standard nose mounted landing light center po...

Page 256: ...te altitude may be at any altitude equal to or higher than the takeoff base altitude provided that the descent from the peak altitude flown does not exceed 7700 feet NOTE Each float cell has a pressure relief valve nominal setting of 5 psig If the above noted allowable decrease in altitude is exceeded minimum operational float pressure 2 0 psig may not be available should the relief valve function...

Page 257: ...or temperature change 25 B 15 x 0 5 psig 0 8 psig Minimum float inflation pressure for this operation would be 2 0 psig 0 8 psig 2 8 psig NOTE Temperature increase will increase float inflation pressure and need not be considered Center of gravity C G Envelope NOTE The installation of the float kit contributes toan aft shift of the C G For conditions requiring pilot only operations ballast will be...

Page 258: ...110 92 10 124 101 20 112 94 30 103 NO FLIGHT 40 115 91 45 110 93 FOR AUTOROTATION VNE REDUCE SPEED BY 2K 85K MIN DO NOT EXCEED CHART VNE UTILITY FLOATS VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 2001 TO 2500 C 0 2 4 6 8 10 12 14 16 18 30 127 122 118 110 94 20 121 102 86 10 110 94 0 130 121 102 87 10 111 94 20 123 103 88 30 112 96 83 NO FLIGHT 40 125 105 90 45 120 102 87 FOR AUTOROTATION VNE REDUC...

Page 259: ...VNE REDUCE SPEED BY 2K 95K MIN DO NOT EXCEED CHART VNE Figure 9 11 VNE Placards Sheet 2 of 2 Kit combination limitations The Passenger Step Kit 369H90060 may not be installed in combination with utility floats The Cargo Hook Kit may be used in combination with the utility floats With an external load on the hook the VNE limitations of the Cargo Hook Kit apply Ref Figure 9 1 The external load on th...

Page 260: ...yaw If emergency occurs at night over water the dual landing lights should not be illuminated above 1000 feet altitude in order to preserve battery power PART IV NORMAL PROCEDURES Rotor engagement on water Determine that sufficient clearance exists between the helicopter and any obstacle during engine start Tail swing before directional control is ob tained will be approximately 200 degrees Landin...

Page 261: ... conditions to stop heli copter during water taxi The use of aft longitudinal cyclic is not completely effective under all conditions Rotor brake application on water Determine that sufficient clearance exists between the helicopter and any obstacle during rotor brake application Azimuth change will be approxi mately 200 nose left PART V PERFORMANCE DATA Hover performance Refer to Section V for IG...

Page 263: ...MD 500E Model 369E Revision 14 9 47 FAA Approved 20 40 60 80 100 120 140 160 180 0 20 40 60 80 100 120 140 160 180 INDICATED AIRSPEED KNOTS CORRECTED FOR INSTRUMENT ERROR F03 047 CALIBRATED AIRSPEED KNOTS Figure 9 13 Airspeed Calibration Curve Utility Floats Installed ...

Page 264: ...8 FAA Approved 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 ...

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