R44 Pilot's Operating Handbook

This handbook has been divided into ten numbered sections. Limitations and emergency procedures have been placed ahead of normal procedures, performance, and other sections to provide easier access to that information. Provisions for expansion of the handbook have been made by deliberate omission of certain paragraph numbers, figure numbers, item numbers, and pages noted as being intentionally blank. REVISED: 10 JUL 2012 1-1 ROBINSON MODEL R44 CAUTIONS AND NOTES SECTION 1 GENERAL Cautions and Notes emphasize important information and are used as follows: CAUTION Equipment damage, injury, or death can result if procedure or instruction is not followed. NOTE Provides emphasis or supplementary infor- mation. REVISED: 10 JUL 2012 1-2 ROBINSON MODEL R44 REVISED: 26 JAN 2024 1-3 R44 EXTERNAL DIMENSIONS (LATER AIRCRAFT SHOWN) EXTERNAL DIMENSIONS SECTION 1 GENERAL ROBINSON MODEL R44 REVISED: 11 MAY 2020 1-4 DESCRIPTIVE DATA MAIN ROTOR Articulation Free to teeter and cone, rigid inplane Number of Blades 2 Diameter 33 feet Blade Chord 10.0 inches inboard, 10.6 inches outboard Blade Twist -6 Degrees Tip Speed at 102% RPM 705 feet per second TAIL ROTOR Articulation Free to teeter, rigid inplane Number of Blades 2 Diameter 58 inches Blade Chord 5.1 inches (constant) Blade Twist 0 Precone Angle 1 Degree Tip Speed at 102% RPM 614 feet per second DRIVE SYSTEM Engine to Upper Sheave: Four double Vee-belts with 0.778:1 speed reducing ratio Upper Sheave to Drive Line: Sprag-type overrunning clutch Drive Line to Main Rotor: Spiral-bevel gears with 11:57 speed reducing ratio Drive Line to Tail Rotor: Spiral-bevel gears with 31:27 speed increasing ratio SECTION 1 GENERAL ROBINSON MODEL R44 SECTION 1 GENERAL REVISED: 16 APR 2003 1-5 DESCRIPTIVE DATA (cont’d) POWERPLANT Model: Lycoming 0-540-F1B5 Type: Six cylinder, horizontally opposed, direct drive, air cooled, carbureted, normally aspirated Displacement: 541.5 cubic inches Normal rating: 260 BHP @ 2800 RPM Maximum continuous rating in R44: 205 BHP at 2718 RPM (102% on tachometer) 5 Minute takeoff rating in R44: 225 BHP at 2718 RPM Cooling system: Direct drive squirrel-cage blower FUEL Approved fuel grades and capacity: See Section 2. OIL Approved oil grades and capacity: See Section 8. ROBINSON MODEL R44 SECTION 1 GENERAL REVISED: 21 OCT 2016 1-6 PERFORMANCE DEFINITIONS KIAS Knots Indicated Airspeed is speed shown on the airspeed indicator. KCAS Knots Calibrated Airspeed is speed shown on the air- speed indicator corrected for instrument and position error. (See Section 5 for position error correction.) KTAS Knots True Airspeed is airspeed relative to undisturbed air. It is KCAS corrected for pressure altitude and temperature. Vne Never-Exceed Airspeed. Vy Speed for best rate of climb. Vh Stabilized level-flight speed at maximum continuous power. MSL Altitude Altitude above mean sea level, indicated by the altimeter (corrected for instrument error) when the barometric subscale is set to the atmospheric pressure existing at sea level. Pressure Altitude Altitude indicated by the altimeter (corrected for instrument error) when the barometric subscale is set to 29.92 inches of mercury (1013.2 mb). Density Altitude Altitude in ISA conditions at which the air would have the same density (it is pressure altitude corrected for OAT). ISA International Standard Atmosphere exists when pressure is 29.92 inches of mercury at sea level, temperature is 15°C at sea level, and temperature decreases 1.98°C per 1000 feet of altitude. BHP Brake Horsepower is actual power output of the engine. MAP Manifold Absolute Pressure is the absolute pressure in the engine intake manifold. RPM Revolutions Per Minute or speed of engine or rotor. (Shown by tachometer as percentage of 2665 engine RPM and 400 main rotor RPM). MCP Maximum Continuous Power. TOP Takeoff Power (limited to 5 minutes in the R44). Critical Altitude Altitude at which full throttle produces maximum allowable power (MCP or TOP). TOGW Takeoff Gross Weight. ROBINSON MODEL R44 SECTION 1 GENERAL REVISED: 5 OCT 2011 1-7 PERFORMANCE DEFINITIONS (cont’d) OAT Outside Air Temperature CAT Carburetor Air Temperature CHT Cylinder Head Temperature GPH Gallons Per Hour AGL Above Ground Level IGE In Ground Effect OGE Out of Ground Effect ALT Alternator WEIGHT AND BALANCE DEFINITIONS Reference Datum A vertical plane from which horizontal distances are measured for balance purposes. The longitudinal reference datum is 100 inches forward of the main rotor shaft centerline for the R44. Station Fore-and-aft location along the helicopter fuselage given in terms of distance in inches from the longitudinal reference datum. Arm Horizontal distance from a reference datum to the center of gravity (CG) of an item. Moment The weight of an item multiplied by its arm. Center of Gravity (CG) Location on the fuselage (usually expressed in inches from the reference datum) at which the helicopter would balance. CG is calculated by dividing the total helicopter moment by total helicopter weight. CG Limits Extreme CG locations within which the helicopter must be operated at a given weight. Usable Fuel Fuel available for flight planning. Unusable Fuel Fuel remaining in the tank that cannot reliably provide uninterrupted fuel flow in the critical flight attitude. Standard Empty Weight Weight of a standard helicopter including unusable fuel, full operating fluids, and full engine oil. Basic Empty Weight Standard empty weight plus weight of installed op- tional equipment. Payload Weight of occupants, cargo, and baggage. Useful Load Difference between maximum gross weight and basic empty weight. ROBINSON MODEL R44 SECTION 1 GENERAL REVISED: 21 OCT 2016 1-8 CONVERSION TABLES METRIC TO ENGLISH Multiply By To Obtain centimeters (cm) 0.3937 inches (in) kilograms (kg) 2.2046 pounds (lb) kilometers 0.5400 nautical miles kilometers 0.6214 statute miles (mi) liters 0.2642 gallons, U.S. (gal) liters 1.0567 quarts (qt) meters 3.2808 feet (ft) millibars (mb) 0.0295 inches of mercury (in. Hg) ENGLISH TO METRIC Multiply By To Obtain feet (ft) 0.3048 meters gallons, U.S. (gal) 3.7854 liters inches (in) 2.5400 centimeters (cm) inches (in) 25.4000 millimeters (mm) inches of mercury (in. Hg) 33.8639 millibars (mb) nautical miles 1.8520 kilometers pounds (lb) 0.4536 kilograms (kg) quarts (qt) 0.9464 liters statute miles (mi) 1.6093 kilometers 1 nautical mile = 1.1508 statute miles 1 statute mile = 0.8690 nautical mile TEMPERATURE °F = 9/5 (°C) + 32 °C = 5/9 (°F – 32) ROBINSON MODEL R44 General SECTION 2 LIMITATIONS CONTENTS SECTION 2 LIMITATIONS Page 2-1 Color Code for Instrument Markings . . . . . . . . . . . . 2-1 Airspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Rotor Speed Limits 2-2 Powerplant Limitations . . . . . . . . . . . . . . . . . . . . . 2-2 Weight Limits 2-3 Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . 2-3 Flight and Maneuver Limitations 2-5 Kinds of Operation Limitations . . . . . . . . . . . . . . . . 2-6 Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6 Instrument Markings ....................... 2-7 Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9 FAA APPROVED: 16 APR 2003 2-i INTENTIONALLY BLANK ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 21 OCT 2016 2-1 SECTION 2 LIMITATIONS GENERAL This section includes operating limitations, instrument markings, and basic placards required for safe operation of the helicopter, its engine, and other standard systems. This helicopter is approved as a normal category rotorcraft under FAA Type Certificate No. H11NM as Model R44 in the serial number range 0002 to 9999. COLOR CODE FOR INSTRUMENT MARKINGS Red Operating limit. Edge of red line indicates limit. Pointer should not enter red during normal operation. Red Cross- hatch Power-off Vne. Yellow Precautionary or special operating procedure range. Green Normal operating range. AIRSPEED LIMITS NEVER-EXCEED AIRSPEED (Vne) 2200 lb (998 kg) TOGW and below 130 KIAS Over 2200 lb (998 kg) TOGW 120 KIAS Autorotation 100 KIAS For Vne reductions with altitude and temperature, see placard on page 2-9. ADDITIONAL AIRSPEED LIMITS 100 KIAS maximum at power above MCP. 100 KIAS maximum with any combination of cabin doors removed. ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 7 MAY 2019 2-2 ROTOR SPEED LIMITS Power On Maximum Minimum* 102% (408 RPM) 101% (404 RPM)** Power Off Maximum Minimum 108% (432 RPM) 90% (360 RPM) *Transient operation at lower RPM permitted for emergency procedures training. **99% (396 RPM) permitted on R44s with tachometers showing engine green arc from 99% to 102%. POWERPLANT LIMITATIONS ENGINE One Lycoming Model O-540-F1B5 OPERATING LIMITS Engine Speed Maximum continuous 102% (2718 RPM) Maximum transient*** 105% (2800 RPM) Cylinder Head Max Temperature 500°F (260°C) Oil Maximum Temperature 245°F (118°C) Oil Pressure Minimum during idle 25 psi Minimum during flight 55 psi Maximum during flight 95 psi Maximum during start & warm up 115 psi Oil Quantity, minimum for takeoff 7 qt (6.6 liters) Manifold Pressure: See placard on page 2-9 for MAP schedule. ***Intentional operation above maximum continuous speed prohibited. FAA APPROVED: 21 FEB 2014 2-3 ROBINSON MODEL R44 SECTION 2 LIMITATIONS WEIGHT LIMITS Maximum gross weight 2400 lb (1089 kg) Minimum gross weight 1550 lb (703 kg) Maximum per seat including baggage compartment 300 lb (136 kg) Maximum in any baggage compartment 50 lb (23 kg) CENTER OF GRAVITY (CG) LIMITS See figure on page 2-4. Reference datum is 100 inches forward of main rotor shaft centerline. NOTE With all doors installed, a solo pilot weight of 150 lb (68 kg) or greater will ensure CG within limits. For lower pilot weight, compute weight and balance; removable ballast may be required to obtain CG at or forward of aft limit. (See Loading Instructions in Section 6.) FAA APPROVED: 21 FEB 2014 2-4 ROBINSON MODEL R44 SECTION 2 LIMITATIONS CENTER OF GRAVITY LIMITS ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 26 JAN 2024 2-5 FLIGHT AND MANEUVER LIMITATIONS Aerobatic flight prohibited. CAUTION Abrupt control inputs may produce high fatigue stresses and cause catastrophic failure of a critical component. Low-G cyclic pushovers prohibited. CAUTION A pushover (forward cyclic maneuver) performed from level flight or following a pull-up causes a low-G (near weightless) condition which can result in catastrophic loss of lateral control. To eliminate a low-G condition, immediately apply gentle aft cyclic. Should a roll commence during a low-G condition, apply gentle aft cyclic to reload rotor before applying lateral cyclic to stop roll. Flight prohibited with governor selected off, with exceptions for in-flight system malfunction or emergency procedures training. Flight in known icing conditions prohibited. Maximum operating density altitude 14,000 feet. Maximum operating altitude 9000 feet AGL to allow landing within 5 minutes in case of fire. Alternator, RPM governor, low rotor RPM warning system, OAT gage, and hydraulic control system must be operational for dispatch. Minimum crew is one pilot in the right front seat. A flight instructor may act as pilot in command from the left front seat. Solo flight from right seat only. Forward left seat belt must be buckled. Operation up to 100 KIAS approved with any combination of cabin doors removed. All seat belts must be buckled and loose items in cabin must be properly secured during doors-off flight. A functioning headset must be worn by each pilot. ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 7 MAY 2018 2-6 KINDS OF OPERATION LIMITATIONS VFR day and night operations are approved. VFR operation at night is permitted only when landing, navigation, instrument, and anti-collision lights are operational. Orientation during night flight must be maintained by visual reference to ground objects illuminated solely by lights on the ground or adequate celestial illumination. Note: There may be additional requirements in countries outside the United States. FUEL LIMITATIONS APPROVED FUEL GRADES Grade Color Specification 100 Green ASTM D910 100LL Blue 100VLL Blue UL 91 Clear to Yellow (no dye) ASTM D7547 UL 94 HJELMCO 91/96 UL Clear to Yellow (no dye) Hjelmco Oil, Inc. Sollentuna, Sweden 91 Yellow TU 38.5901481-96 Ukrainian National Standard B91/115 Green GOST 1012-72 Russian National Standard B95/130 Amber ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 7 MAY 2018 2-7 FUEL LIMITATIONS (cont’d) FUEL CAPACITY Total Capacity US gallons (liters) Usable Capacity US gallons (liters) Tanks with bladders: Main tank Auxiliary tank Combined capacity 30.5 17.2 47.7 (115) (65) (180) 29.5 17.0 46.5 (112) (64) (176) Tanks without bladders: Main tank Auxiliary tank Combined capacity 31.6 18.5 50.1 (120) (70) (190) 30.6 18.3 48.9 (116) (69) (185) Note: Per R44 Service Bulletin SB-78B, fuel tanks without bladders should no longer be in service. INSTRUMENT MARKINGS NOTE Red lines offset so instrument pointer should not enter red. See color code on page 2-1. AIRSPEED INDICATOR Green arc 0 to 110 KIAS Yellow arc* 110 to 130 KIAS Red cross-hatch 100 KIAS Red line 130 KIAS *Earlier airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 110 KIAS EXCEPT IN SMOOTH AIR ROTOR TACHOMETER Lower red line 90% Green arc 90 to 108% Upper red line 108% ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 7 MAY 2018 2-8 INSTRUMENT MARKINGS (cont’d) ENGINE TACHOMETER** Lower red line 101% Green arc 101 to 102% Upper red line 102% **Earlier tachometers show green arc from 99 to 102% and lower red line at 99%. OIL PRESSURE Lower red line 25 psi Lower yellow arc 25 to 55 psi Green arc 55 to 95 psi Upper yellow arc 95 to 115 psi Upper red line 115 psi OIL TEMPERATURE Green arc 75 to 245°F (24 to 118°C) Red line 245°F (118°C) CYLINDER HEAD TEMPERATURE Green arc 200 to 500°F (93 to 260°C) Red line 500°F (260°C) MANIFOLD PRESSURE Green arc 16.0 to 24.7 in. Hg Yellow arc 21.8 to 26.3 in. Hg Red line 26.3 in. Hg Yellow arc denotes variable MAP limits. See placard on page 2-9. CARBURETOR AIR TEMPERATURE Yellow arc –19°C to + 3°C ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 17 DEC 2019 2-9 PLACARDS In clear view and readable by pilot in flight: Note: Earlier placards do not include MAP and airspeed limits at -30°C. ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 7 MAY 2018 2-10 PLACARDS (cont’d) Near main fuel tank filler cap: FUEL 100 OCT MIN GRADE AVIATION GASOLINE or FUEL AVIATION GASOLINE – GRADE 100 LL OR SEE PILOT’S HANDBOOK Near aux fuel tank filler cap: AUX FUEL 100 OCT MIN GRADE AVIATION GASOLINE or AUX FUEL AVIATION GASOLINE – GRADE 100 LL OR SEE PILOT’S HANDBOOK Near fuel shut-off valve: FUEL On fuel shut-off valve: ON OFF Near main tank fuel gage: For bladder style tank 29.5 US GAL For aluminum (non-bladder) tank 30.6 US GAL ROBINSON MODEL R44 FAA APPROVED: 21 OCT 2016 2-11 PLACARDS (cont’d) Near aux tank fuel gage: For bladder-style tank AUX 17.0 US GAL For aluminum (non-bladder) tank AUX 18.3 US GAL In clear view of pilot: MINIMUM SOLO PILOT WEIGHT 150 LB (SEE PILOT’S HANDBOOK) or SEE PILOT’S HANDBOOK FOR SOLO PILOT WEIGHT LESS THAN 150 LB (68 KG) THIS ROTORCRAFT APPROVED FOR DAY AND NIGHT VFR OPERATIONS LOW-G PUSHOVERS PROHIBITED On removable cyclic grip: SOLO FROM RIGHT SEAT ONLY On or near collective controls: NO STOWAGE KEEP AREA CLEAR On aircraft without ashtray, in clear view of all occupants: NO SMOKING On aircraft with ashtray, in clear view of all occupants: NO SMOKING IN FRONT SEATS ROBINSON MODEL R44 SECTION 2 LIMITATIONS FAA APPROVED: 21 FEB 2014 2-12 ROBINSON MODEL R44 SECTION 2 LIMITATIONS PLACARDS (cont’d) Inside each baggage compartment: CAUTION DO NOT EXCEED ANY OF THE FOLLOWING: • COMPARTMENT CAPACITY: 50 LB MAX • COMBINED SEAT PLUS COMPARTMENT: 300 LB MAX • ROTORCRAFT GROSS WEIGHT LIMIT SEE ROTORCRAFT FLIGHT MANUAL FOR ADDITIONAL LOADING INSTRUCTIONS. ROBINSON MODEL R44 FAA APPROVED: 11 MAY 2020 3-i ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES CONTENTS Page Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Power Failure – General . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Power Failure Above 500 Feet AGL . . . . . . . . . . . . . . . . 3-2 Power Failure Between 8 Feet and 500 Feet AGL . . . . . 3-2 Power Failure Below 8 Feet AGL . . . . . . . . . . . . . . . . . . 3-3 Maximum Glide Distance Configuration . . . . . . . . . . . . . 3-3 Minimum Rate of Descent Configuration . . . . . . . . . . . . 3-3 Air Restart Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3 Emergency Water Landing – Power Off . . . . . . . . . . . . . 3-4 Emergency Water Landing – Power On . . . . . . . . . . . . . 3-4 Loss of Tail Rotor Thrust in Forward Flight . . . . . . . . . . . 3-5 Loss of Tail Rotor Thrust in Hover . . . . . . . . . . . . . . . . . 3-5 Headset Audio Failure . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 Engine Fire During Start on Ground . . . . . . . . . . . . . . . . 3-6 Engine Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Electrical Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Tachometer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Hydraulic System Failure . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Governor Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Warning/Caution Lights . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11 INTENTIONALLY BLANK ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 OCT 2016 3-1 SECTION 3 EMERGENCY PROCEDURES DEFINITIONS Land Immediately – Land on the nearest clear area where a safe normal landing can be performed. Be prepared to enter autorotation during approach, if required. Land as soon as practical – Landing site is at pilot’s discretion based on nature of problem and available landing areas. Flight beyond nearest airport is not recommended. POWER FAILURE – GENERAL A power failure may be caused by either an engine or drive system failure and will usually be indicated by the low RPM horn. An engine failure may be indicated by a change in noise level, nose left yaw, an oil pressure light, or decreasing engine RPM. A drive system failure may be indicated by an unusual noise or vibration, nose right or left yaw, or decreasing rotor RPM while engine RPM is increasing. In case of power failure, immediately lower collective to enter autorotation and reduce airspeed to power-off Vne or below. CAUTION Aft cyclic is required when collective is lowered at high airspeed. CAUTION Do not apply aft cyclic during touchdown or ground slide to prevent possible blade strike to tailcone. ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-2 POWER FAILURE ABOVE 500 FEET AGL 1. Lower collective immediately to maintain rotor RPM. 2. Establish a steady glide at approximately 70 KIAS. (For maximum glide distance or minimum rate of descent, see page 3-3.) 3. Adjust collective to keep RPM between 97 and 108% or apply full down collective if light weight prevents attaining above 97%. 4. Select landing spot and, if altitude permits, maneuver so landing will be into wind. 5. A restart may be attempted at pilot’s discretion if sufficient time is available (See “Air Restart Procedure”, page 3-3). 6. If unable to restart, turn unnecessary switches and fuel valve off. 7. At about 40 feet AGL, begin cyclic flare to reduce rate of descent and forward speed. 8. At about 8 feet AGL, apply forward cyclic to level ship and raise collective just before touchdown to cushion landing. Touch down in level attitude with nose straight ahead. POWER FAILURE BETWEEN 8 FEET AND 500 FEET AGL 1. Lower collective immediately to maintain rotor RPM. 2. Adjust collective to keep RPM between 97 and 108% or apply full down collective if light weight prevents attaining above 97%. 3. Maintain airspeed until ground is approached, then begin cyclic flare to reduce rate of descent and forward speed. 4. At about 8 feet AGL, apply forward cyclic to level ship and raise collective just before touchdown to cushion landing. Touch down in level attitude and nose straight ahead. FAA APPROVED: 21 FEB 2014 3-3 ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES POWER FAILURE BELOW 8 FEET AGL 1. Apply right pedal as required to prevent yawing. 2. Allow rotorcraft to settle. 3. Raise collective just before touchdown to cushion landing. MAXIMUM GLIDE DISTANCE CONFIGURATION 1. Airspeed approximately 90 KIAS. 2. Rotor RPM approximately 90%. 3. Best glide ratio is about 4.7:1 or one nautical mile per 1300 feet AGL. MINIMUM RATE OF DESCENT CONFIGURATION 1. Airspeed approximately 55 KIAS. 2. Rotor RPM approximately 90%. 3. Minimum rate of descent is about 1350 feet per minute. Glide ratio is about 4:1 or one nautical mile per 1500 feet AGL. CAUTION Increase rotor RPM to 97% minimum when autorotating below 500 feet AGL. AIR RESTART PROCEDURE CAUTION Do not attempt restart if engine malfunction is suspected or before safe autorotation is established. 1. Mixture - full rich. 2. Throttle- closed, then cracked slightly. 3. Actuate starter with left hand. FAA APPROVED: 21 FEB 2014 3-4 ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES EMERGENCY WATER LANDING – POWER OFF 1. Follow same procedures as for power failure over land until contacting water. If time permits, unlatch doors prior to water contact. 2. Apply lateral cyclic when aircraft contacts water to stop rotors. 3. Release seat belt and quickly clear aircraft when rotors stop. EMERGENCY WATER LANDING – POWER ON 1. Descend to hover above water. 2. Unlatch doors. 3. Passengers exit aircraft. 4. Fly to safe distance from passengers to avoid possible injury by rotors. 5. Switch battery and alternator OFF. 6. Roll throttle off into overtravel spring. 7. Keep aircraft level and apply full collective as aircraft contacts water. 8. Apply lateral cyclic to stop rotors. 9. Release seat belt and quickly clear aircraft when rotors stop. ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 17 DEC 2019 3-5 LOSS OF TAIL ROTOR THRUST IN FORWARD FLIGHT Failure is usually indicated by nose right yaw which cannot be corrected by applying left pedal. 1. Immediately enter autorotation. 2. Maintain at least 70 KIAS if practical. 3. Select landing site, roll throttle off into overtravel spring, and perform autorotation landing. NOTE When a suitable landing site is not available, the vertical stabilizers may permit limited controlled flight at low power settings and airspeeds above 70 KIAS; however, prior to reducing airspeed, enter full autorotation. LOSS OF TAIL ROTOR THRUST IN HOVER Failure is usually indicated by nose right yaw which cannot be stopped by applying left pedal. 1. Immediately roll throttle off into overtravel spring and allow aircraft to settle. 2. Raise collective just before touchdown to cushion landing. HEADSET AUDIO FAILURE If headset audio fails, land as soon as practical. CAUTION For aircraft which provide low RPM horn through the audio system, pilot will not hear horn with a failed headset. ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 OCT 2016 3-6 ENGINE FIRE DURING START ON GROUND 1. Cranking – Continue and attempt to start which would suck flames and excess fuel into engine. 2. If engine starts, run at 60-70% RPM for a short time. 3. Fuel mixture – OFF. 4. Fuel valve – OFF. 5. Battery switch – OFF. 6. If time permits, apply rotor brake to stop rotors. 7. Exit helicopter. ENGINE FIRE IN FLIGHT 1. Enter autorotation. 2. Cabin heat – OFF (if time permits). 3. Cabin vent – ON (if time permits). 4. If engine is running, perform normal landing, then fuel mixture OFF and fuel valve OFF. If engine stops running, fuel valve OFF and complete autorotation landing. 5. Battery switch – OFF. 6. If time permits, apply rotor brake to stop rotors. 7. Exit helicopter. ELECTRICAL FIRE IN FLIGHT 1. Battery and alternator switches – OFF. 2. Open cabin vents. 3. Land immediately. 4. Fuel mixture OFF and fuel valve OFF. 5. If time permits, apply rotor brake to stop rotors. 6. Exit helicopter. NOTE Low RPM warning system and governor are inoperative with battery and alternator switches both off. ROBINSON MODEL R44 TACHOMETER FAILURE If rotor or engine tach malfunctions in flight, use remaining tach to monitor RPM. If it is not clear which tach is malfunctioning or if both tachs malfunction, allow governor to control RPM and land as soon as practical. NOTE Each tach, the governor, and the low RPM horn are on separate power circuits. A special circuit allows the battery to supply power to the tachs with the battery and alternator switches both off. HYDRAULIC SYSTEM FAILURE Hydraulic system failure is indicated by heavy or stiff cyclic and collective controls. Loss of hydraulic fluid may cause intermittent and/or vibrating feedback in the controls. Control will be normal except for the increase in stick forces. 1. HYD Switch – verify ON. 2. If hydraulics not restored, HYD Switch – OFF. 3. Adjust airspeed and flight condition as desired for comfortable control. 4. Land as soon as practical. GOVERNOR FAILURE If engine RPM governor malfunctions, grip throttle firmly to override the governor, then switch governor off. Complete flight using manual throttle control. ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 17 DEC 2019 3-7 ROBINSON MODEL R44 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 5 NOV 1999 3-8 WARNING/CAUTION LIGHTS NOTE If a light causes excessive glare at night, bulb may be unscrewed or circuit breaker pulled to eliminate glare during landing. OIL Indicates loss of engine power or oil pressure. Check engine tach for power loss. Check oil pressure gage and, if pressure loss is confirmed, land immediately. Continued operation without oil pressure will cause serious engine damage and engine failure may occur. ENG FIRE Indicates possible fire in the engine compart- ment. See procedures on page 3-6. MR TEMP Indicates excessive temperature of main rotor gearbox. See note below. MR CHIP Indicates metallic particles in main rotor gearbox. See note below. TR CHIP Indicates metallic particles in tail rotor gearbox. See note below. NOTE If light is accompanied by any indication of a problem such as noise, vibration, or temperature rise, land immediately. If there is no other indication of a problem, land as soon as practical. Break-in fuzz will occasionally activate chip lights. If no metal chips or slivers are found on detector plug, clean and reinstall (tail gearbox must be refilled with new oil). Hover for at least 30 minutes. If chip light comes on again, replace gearbox before further flight.