MD Helicopters 369FF Flight Manual Download Page 32

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CSP–FF–1

ROTORCRAFT FLIGHT MANUAL

General

MD 530F Plus

(Model 369FF)

Revision 5

1–14

NOTES:

ALL

DIMENSIONS IN FEET

1. HELICOPTER ON GROUND WITH

FULL

FUEL.

TYPICAL

TTITUDE

OF CARGO DECK 5.3 DEGREES

NOSE UP

IF OPTIONAL

EXTENDED

LANDING GEAR IS INST

ALLED,

ADD 0.87 FEET

ALL

VER

TICAL

DIMENSIONS.

F04−001

Figure 1–1. MD 530F Plus Principal Dimensions – Standard Landing Gear

Summary of Contents for 369FF

Page 1: ...n inserted into your manu al before posting Revision 5 REMOVE PAGES INSERT PAGES FRONT MATTER F i thru F xiv F i thru F xiv SECTION I All pages New Revision 5 Pages SECTION II 2 5 2 6 2 5 2 6 SECTION...

Page 2: ......

Page 3: ...IONS AS SET FORTH IN SECTION 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 A...

Page 4: ...vision 1 11 April 1990 Revision 2 29 May 1990 Revision 3 17 August 1990 Revision 4 1 April 1992 Revision 5 17 July 1995 Reissue 1 14 August 1998 Revision 1 8 January 1999 Revision 2 30 December 1999 R...

Page 5: ...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...

Page 6: ...ergency 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 1...

Page 7: ...Data 5 1 General 5 1 5 2 Density Altitude 5 2 5 3 Airspeed Calibration 5 4 5 4 Speed For Best Rate of Climb 5 6 5 5 Hover Ceiling VS Gross Weight In ground Effect IGE 5 8 5 6 Height Velocity Diagram G...

Page 8: ...5 7 12 Cleaning Fuselage Interior Trim and Upholstery 7 15 7 13 Cleaning Aircraft Exterior and Rotor Blades 7 16 7 14 Cleaning Canopy and Door Transparent Plastic 7 16 7 15 Fluid Leak Analysis 7 16 7...

Page 9: ...Paragraph 2 10 Revised fuel specifications Section III Removed company logo from all pages Paragraph 3 9 Added malfunctions procedures for low engine oil pressure and loss of torque indication Section...

Page 10: ...5 F ii Revision 5 F iii Revision 4 F iv Revision 5 F v Revision 4 F vi Revision 5 F vii Revision 5 F viii Revision 5 F ix Revision 5 F x Revision 5 F xi Revision 5 F xii Revision 5 F xiii Revision 5 F...

Page 11: ...sion 5 1 17 Revision 5 1 18 Revision 5 1 19 Revision 5 1 20 Revision 5 1 21 1 22 blank Revision 5 II 2 i 2 ii blank Revision 4 2 1 Revision 4 2 2 Revision 4 2 3 Revision 4 2 4 Revision 4 2 5 Revision...

Page 12: ...n 5 3 8 Revision 5 3 9 Revision 5 3 10 Revision 5 3 11 Revision 5 3 12 Revision 5 3 13 Revision 5 3 14 Revision 5 3 15 Revision 5 3 16 Revision 5 3 17 Revision 5 3 18 Revision 5 3 19 Revision 5 3 20 R...

Page 13: ...ision 4 4 12 Revision 4 4 13 Revision 4 4 14 Revision 4 4 15 Revision 4 4 16 Revision 5 4 17 Revision 4 4 18 Revision 4 4 19 Revision 4 4 20 Revision 4 4 21 Revision 4 4 22 Revision 4 4 23 Revision 4...

Page 14: ...Revision 4 5 13 Revision 4 5 14 Revision 4 5 15 Revision 4 5 16 Revision 4 5 17 Revision 4 5 18 Revision 4 5 19 Revision 4 5 20 Revision 4 5 21 Revision 4 5 22 Revision 4 5 23 Revision 4 5 24 Revisio...

Page 15: ...evision 4 6 19 Revision 4 6 20 Revision 4 6 21 Revision 4 6 22 Revision 4 6 23 6 24 blank Revision 4 VII 7 i 7 ii blank Revision 5 7 1 Revision 5 7 2 Revision 5 7 3 Revision 5 7 4 Revision 5 7 5 Revis...

Page 16: ...ion 5 8 2 Revision 5 8 3 Revision 5 8 4 Revision 5 IX 9 i 9 ii blank Revision 5 9 1 Revision 5 9 2 Revision 5 9 3 Revision 5 9 4 Revision 5 9 5 Revision 5 9 6 Revision 5 9 7 Revision 5 9 8 Revision 5...

Page 17: ...m 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 530F Plus Principal...

Page 18: ......

Page 19: ...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 Transp...

Page 20: ...List 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 pilo...

Page 21: ...re 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 MAINTEN...

Page 22: ...articular 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 DEFI...

Page 23: ...eters 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 Fahrenh...

Page 24: ...bar 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 Positio...

Page 25: ...s is done by revision The List of 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...

Page 26: ...ed 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 source...

Page 27: ...one pilot seated on the left side of the cockpit The passengers sit to the right abreast of the pilot Seat belts are provided for all positions In the military version the center seat is eliminated A...

Page 28: ...on 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...

Page 29: ...neric system 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 syst...

Page 30: ...rotor 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 453 NR On aircraft equipped with a generic wir...

Page 31: ...e 7 2 1 6 1 9 12 5 5 7 Total 242 53 3 64 0 416 0 188 7 Table 1 2 Fuel System Optional Self Sealing Fuel Tanks Fuel Type Liters Imp Gal U S Gal Pounds Kilograms Jet A Usable 226 8 49 9 59 9 407 0 184 9...

Page 32: ...OTES ALL DIMENSIONS IN FEET 1 HELICOPTER ON GROUND WITH 2 FULL FUEL TYPICAL ATTITUDE OF CARGO DECK 5 3 DEGREES NOSE UP IF OPTIONAL EXTENDED LANDING GEAR IS INSTALLED ADD 0 87 FEET TO ALL VERTICAL DIME...

Page 33: ...0 160 140 120 100 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...

Page 34: ...TEMPERATURE 50 F METHOD ENTER AT 50 F READ 10 C ACROSS ON C SCALE METHOD MAY BE REVERSED TO FIND F WHEN C IS KNOWN ALTERNATE METHOD F 9 5 X C 32 C 5 9 F 32 TEMPERATURE EXAMPLE F C 140 120 100 80 60 40...

Page 35: ...0 90 340 69 344 47 348 26 352 05 355 83 359 62 363 40 367 19 370 97 374 76 100 378 54 382 33 386 11 389 90 393 69 397 47 401 26 405 04 408 83 412 61 110 416 40 420 18 423 97 427 75 431 54 435 62 439 1...

Page 36: ...28 651 28 955 29 260 29 565 29 870 30 174 100 30 479 30 784 31 089 31 394 31 698 32 003 32 308 32 613 32 918 33 222 Table 1 6 Weight Pounds to Kilograms 0 1 2 3 4 5 6 7 8 9 Pounds Kilo grams Kilo gra...

Page 37: ...S CONVERT KNOTS TO METERS SEC KNOWN WIND SPEED 25 KT METHOD ENTER CHART AT 25 KT READ APPROXIMATELY 13 METERS SEC ACROSS ON METERS SEC SCALE METHOD MAY BE REVERSED TO FIND KNOTS WHEN METERS SEC ARE KN...

Page 38: ...29 2 29 1 29 0 28 9 28 7 28 6 28 5 28 4 28 3 28 2 28 1 28 0 28 8 1055 1050 1045 1040 1035 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 3...

Page 39: ...781 86 23 088 0 7716 8000 0 7860 1 1279 0 850 30 471 752 63 22 225 0 7428 9000 0 7620 1 1456 2 831 26 905 724 29 21 388 0 7148 10000 0 7385 1 1637 4 812 23 338 696 82 20 577 0 6877 11000 0 7155 1 1822...

Page 40: ......

Page 41: ...n 1 second During power changes in flight 826 C to 905 C for 12 seconds Gas producer N1 speed limits Maximum continuous 105 Minimum ground idle speed 64 Transient limits 106 for 10 seconds Power Turbi...

Page 42: ...utes OFF 30 seconds ON 30 minutes OFF 2 10 FUEL SYSTEM LIMITATIONS Fuel Specifications The use of AVGAS MIL G 5572 only as an emergency fuel is not allowed Unexpected engine flameout may occur For add...

Page 43: ...eed 3 7 3 6 Emergency Landing Procedures 3 7 Water Landing 3 7 3 7 Fire 3 9 Engine Fire on the Ground 3 10 Engine Fire During Flight 3 11 Cabin Fire Smoke 3 12 3 8 Engine Fuel Control System Malfuncti...

Page 44: ...e 3 20 3 12 Abnormal Vibrations 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...

Page 45: ...crew 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 ac...

Page 46: ...for ENGINE OUT and LOW ROTOR 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 ENGINE OUT AUDIBLE WARNING HORN SEE NOTE CAUTION AND WARNING LIGHTS NOTE ON LATER MODEL 369FF HELCOPTERS ENGINE OUT AUDIBLE WARNING...

Page 47: ...ndicators are actuated when N1 falls below 55 or NR falls below 453 NR Ref 95 1 N2 Procedures Engine Failure In Cruise at 500 Feet AGL or Above F Adjust collective pitch according to altitude and airs...

Page 48: ...lete loss of power time and altitude permitting place twistgrip in cutoff and close fuel shutoff valve F Select landing area and maneuver as required F If operating at reduced rotor RPM to extend glid...

Page 49: ...unt and duration of collective reduction depends upon the airspeed and height above the ground at which the power loss occurs F As the ground is approached flare as required to reduce forward speed an...

Page 50: ...critical Procedures F Close twist grip to cutoff position F Press start ignition button immediately NOTE Pressing the starter button actuates the igniter If N1 is 12 percent or above open twist grip...

Page 51: ...increases in power Governor failure producing an underspeed Procedures F Respond immediately to the low rotor RPM warning by adjusting collec tive to maintain rotor RPM within limits F Check other Cau...

Page 52: ...ns Power on Procedures F Descend to hovering altitude over water F Open doors and push door handle full down to prevent relatching F Passengers and copilot exit aircraft F Fly a safe distance away fro...

Page 53: ...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 p...

Page 54: ...means 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...

Page 55: ...EVACUATE IF TIME AND SITUATION PERMIT F Rotor brake if installed APPLY F Secure area HAVE PASSENGERS AND SPECTATORS MOVE A SAFE DISTANCE FROM THE AIR CRAFT F Fire extinguisher USE AS APPROPRIATE ENGI...

Page 56: ...ional descent to the ground If a power off descent is chosen proceed as follows F Collective DOWN TO ESTABLISH AUTOROTATION TO SELECTED AREA F Twistgrip CUTOFF F Fuel shutoff valve PULL TO CLOSE F Rad...

Page 57: ...ECESSARY F Twistgrip CUTOFF AS SOON AS HELICOPTER IS ON GROUND F BAT EXT switch OFF F Passengers crew EVACUATE IF UNABLE TO LAND IMMEDIATELY AND FIRE SOURCE CAN BE IDENTIFIED F Malfunctioning system O...

Page 58: ...ncreasing Possible right yaw Procedures F Increase collective to load the main rotor simultaneously rolling the twist grip toward the ground idle position until control of N2 speed is obtained F Manua...

Page 59: ...tor RPM in the green 410 508 and at tempt level flight at 60 knots IAS F If power is insufficient for level flight or a power on decent make an au torotational landing Conditions Power Turbine Governo...

Page 60: ...as possible LOW ENGINE OIL PRESSURE Indications Oil pressure decreasing below normal operating range Ref Section II Conditions In flight Procedures F Land as soon as possible F Shut engine down Condi...

Page 61: ...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 F Land as soon as possible M...

Page 62: ...er setting Indications Failure is normally indicated by an uncontrollable by pedal yawing to the right Procedures F Reduce power by lowering collective F Adjust airspeed between 50 to 60 knots F Use l...

Page 63: ...back 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 th...

Page 64: ...ontinued flight Indications Inoperative trim Conditions The trim motor fails to respond to application of the cyclic trim switch in one or more directions Procedures F Establish a safe flight conditio...

Page 65: ...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 tri...

Page 66: ...ed until the cause of the vibration has been identified and corrected 3 13 FUEL SYSTEM MALFUNCTIONS FUEL FILTER Indications Yellow FUEL FILTER indicator ON Conditions A predetermined pressure differen...

Page 67: ...f fuel quantity Procedures F Avoid large steady side slip angles and uncoordinated maneuvers Sideslips may cause fuel starvation and result in unexpected power loss or engine failure Avoid large stead...

Page 68: ...temp relay removes the battery from the DC electrical bus when battery temperature reaches 160 F F Land as soon as possible NOTE No further flights are authorized until battery is inspected and cause...

Page 69: ...ack 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 enable the Engine O...

Page 70: ...en the proper balance between fuel flow and air flow are upset The stall may vary in intensity and usually occurs during a rapid increase in power Procedures F For one or two low intensity pops contin...

Page 71: ...ER 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...

Page 72: ......

Page 73: ...iceable if rubber deterioration or separation or a vibration is noted Evidence of light swelling pock marks and crumbs are surface conditions and are not indications of bearing failure F F Apply teete...

Page 74: ...E COMPARTMENT F Engine mounts mounting pads and firewalls CHECK F Landing gear attach points rear dampers leaks and inflation CHECK F Engine oil air and fuel lines CHECK F Scavenge oil filter bypass i...

Page 75: ...minutes OFF 30 seconds ON 30 minutes OFF F When 12 percent N1 minimum cranking speed is reached open twist grip toward ground idle detent until engine lights off Observe TOT indicator for immediate te...

Page 76: ...conditions favorable for a hot start 5 If an engine fire may be indicated by flames emanating from the tailpipe occurs pull out fuel valve and abort start F Abort start procedures F F Close twistgrip...

Page 77: ...OVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 WEIGHT 3 9 14 D 30 20 10 0 10 20 30 40 50 OAT DEG C 2600 2800 3000 3200 3400 3600 3800 GROSS WEIGHT LB EXAMPL...

Page 78: ...TICAL ALTITUDE PER 10 AMPERE REDUCTION OR INCREASE IN ELECTRICAL LOAD OAT C 5 15 35 WEIGHT 3 9 14 D MAXIMUM GROSS WEIGHT INTERNAL LOAD OPERATION NO WIND 30 20 10 0 10 20 30 40 50 OAT DEG C 2600 2800 3...

Page 79: ...1 Servicing Materials Operating Supplies 7 7 Figure 7 4 Servicing Points Sheet 1 of 2 7 11 Figure 7 4 Servicing Points Sheet 2 of 2 7 12 7 8 Fuel System Servicing 7 13 7 9 Engine Oil System Servicing...

Page 80: ......

Page 81: ...ufficient 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...

Page 82: ...ATION FORWARD SECTION INSTALLATION PILOT DOOR ASSEMBLY HORIZONTAL STABILIZER VERTICAL STABILIZER TAILBOOM AFT SECTION INSTALLATION TAIL ROTOR TRANSMISSION TAIL ROTOR ASSEMBLY ENGINE INSTALLATION MAIN...

Page 83: ...copter 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 F40 030 WARNING BE SURE LOCK SNAPS INTO POSITION SHOWN BEFORE R...

Page 84: ...ising 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 attac...

Page 85: ...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...

Page 86: ...TIE CORD 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 COV...

Page 87: ...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...

Page 88: ...anover NJ 07936 Hatcol 3211 Hatco Corporation King George Post Road Fords New Jersey 08863 BP Turbo Oil 2380 EXXON Turbo Oil 2380 Air BP Castrol Aero Jet5 Castrol Industrial North Ameri ca Specialty P...

Page 89: ...t 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 appr...

Page 90: ...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 r...

Page 91: ...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 GAG...

Page 92: ...2 ENGINE OIL TANK DRAIN ENGINE OIL COOLER DRAIN STATION 137 50 BULKHEAD MAIN TRANSMISSION OIL COOLER DRAIN ENGINE WASH FITTING SCAVENGE OIL FILTER OIL FILTER BYPASS INDICATOR 250 C30 ENGINE ENGINE OI...

Page 93: ...ater 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 tempe...

Page 94: ...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...

Page 95: ...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 FUSE...

Page 96: ...ces 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 attemp...

Page 97: ...n 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 se...

Page 98: ...move 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 Ref Figure 7 5 Open door Remove interior...

Page 99: ...FT FLIGHT MANUAL MD 530F Plus Model 369FF Revision 5 7 19 DOOR FRAME PILOT S DOOR F60 043 PASSENGER CARGO COMPARTMENT DOOR LH SHOWN RH SIMILAR DOOR STRUCTURE DOOR HINGE FUSELAGE STRUCTURE HINGE PIN TA...

Page 100: ...rocess The starter generator can be used to motor the Rolls Royce 250 Series engine for compressor cleaning cycle Input voltage should be 24 vdc but it is permissible to use 12 vdc To prevent starter...

Page 101: ...onds prior to starter engagement F Motor the engine with the twistgrip in CUTOFF F Release starter switch as necessary to maintain between 5 and 10 N1 speed during the wash rinse F Water injection wil...

Page 102: ......

Page 103: ...ADDITIONAL OPERATIONS AND PERFORMANCE DATA TABLE OF CONTENTS PARAGRAPH PAGE 8 1 Hover Ceiling Out of Ground Effect OGE 8 1 Figure 8 1 Hover Ceiling OGE Standard Engine Air Inlet 8 2 Figure 8 2 Hover C...

Page 104: ......

Page 105: ...ability out of ground effect OGE at take off power for known conditions of pressure alti tude and outside air temperature or alternately the maximum hover ceiling for a known gross weight and outside...

Page 106: ...PLE PRESS ALT 8000 FT OAT 6 C ENTER CHART AT 6 C ON OAT SCALE MOVE UP TO 8000 PRESS ALT LINE MOVE RIGHT TO GROSS WEIGHT LINE READ HOVER GROSS WEIGHT 3420 LB MAXIMUM GROSS WEIGHT INTERNAL LOAD OPERATIO...

Page 107: ...ICABLE TO ALL TEMPERATURES PRESSURE ALT FT CABIN HEAT ANTI ICE BOTH SL TO 6000 8000 12000 16000 0 0 0 90 0 0 335 450 0 100 510 603 CONTROLLABILITY LIMIT 3 PERCENT PEDAL MARGIN IN 17 KT SIDEWIND FROM T...

Page 108: ...ION F40 036 CONTROLLABILITY LIMIT 3 PERCENT PEDAL MARGIN IN 17 KT SIDEWIND FROM THE RIGHT REAR QUARTER INCREASE OR DECREASE WEIGHT CAPABILITY POUNDS ABOVE CRITICAL ALTITUDE PER 10 AMPERE REDUCTION OR...

Page 109: ...9 2 9 4 Operating Instructions Cargo Hook Kit 9 3 Figure 9 1 VNE Placards 9 5 Figure 9 2 Cargo Hook Release Electrical and Mechanical 9 6 Figure 9 3 Cargo Hook 9 8 Figure 9 4 Speed for Best Rate of Cl...

Page 110: ......

Page 111: ...emental Data is to be used in conjunction with the basic Flight Manual data and takes precedence over that data when the equip ment is installed Be sure to include a review of the appropriate flight m...

Page 112: ...rator filter CSP FF 1 Cargo hook CSP FF 1 Section IX Emergency floats CSP FF 1 Section IX Indicates data incorporated into the flight manual Sections I thru VII where appropriate 9 3 OPTIONAL EQUIPMEN...

Page 113: ...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...

Page 114: ...3100 pounds center of gravity limits for 3100 pounds apply Cargo Hook Limitations Cargo hook structural load limit is 2000 pounds Airspeed Limitations With no load on hook airspeed limits are unchange...

Page 115: ...PRESS ALT x 1000 GROSS WT 3200 LB OR LESS C 0 2 4 6 8 10 12 14 16 18 20 30 72 56 20 64 10 72 56 0 80 65 49 10 73 57 NO 20 66 51 FLIGHT 30 75 59 40 45 EXTERIOR LOAD VNE IAS KNOTS OAT PRESS ALT x 1000 G...

Page 116: ...mechanical release handle to release cargo in the event of an elec trical failure Operate handle quickly and deliberately NOTE Ground support personnel should manually assure positive reset of the ca...

Page 117: ...ft side of cargo hook body HookAshouldAreturnAtoAtheAclosedApositionAafterAabove checks Move pilot s cyclic to all extreme positions Cargo hook must remain locked and external release knob must not ro...

Page 118: ...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 i...

Page 119: ...argo Hook Kit MD 530F Plus Model 369FF Revision 5 9 9 FAA Approved F40 038 0 50 60 70 80 90 14000 12000 10000 8000 6000 4000 2000 16000 DENSITY ALTITUDE FEET INDICATED AIRSPEED KNOTS CORRECTED FOR INS...

Page 120: ...ing 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 Momen...

Page 121: ...ation 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 prov...

Page 122: ...Operating 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 altitu...

Page 123: ...oss weight of 3000 pounds at Station 103 6 to 1803 pounds at Station 107 2 Placards When emergency floats are installed the following placards are required Placard 1 Placard 2 WARNING FLOAT INFLATION...

Page 124: ...E SPEED BY 22K 85K MIN DO NOT EXCEED CHART VNE FLOATS STOWED VNE IAS KNOTS OAT PRESS ALT X 1000 GROSS WT 1803 TO 2000 LB C 0 2 4 6 8 10 12 14 16 18 30 139 134 129 125 120 116 111 107 103 20 147 142 13...

Page 125: ...49 146 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 86K 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 2101 TO 2200 LB C 0...

Page 126: ...GHT 40 150 147 129 45 149 146 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 88K 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...

Page 127: ...GHT 40 150 147 129 45 149 135 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...

Page 128: ...FLIGHT 40 150 125 105 45 149 120 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 92K 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 GRO...

Page 129: ...O FLIGHT 40 136 112 97 45 129 108 FOR AUTOROTATION VNE REDUCE SPEED BY 22K 94K 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 GR...

Page 130: ...ed at 2 000 feet or less above landing sur face to minimize differential pressure change with altitude change F For over water operation in conditions near the Height Velocity Diagram immediate pilot...

Page 131: ...battery 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...

Page 132: ...GHT HAND SKID LEFT HAND SIMILAR Figure 9 6 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...

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