PILOT'S OPERATING HANDBOOK AND FAA APPROVED ROTORCRAFT FLIGHT MANUAL

procedures, and operational handling characteristics of the helicopter before flight. 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 II 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 REVISED: 26 JAN 2024 1-3 R44 II EXTERNAL DIMENSIONS (LATER AIRCRAFT SHOWN) EXTERNAL DIMENSIONS ROBINSON MODEL R44 II SECTION 1 GENERAL REVISED: 26 JAN 2024 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 ROBINSON MODEL R44 II SECTION 1 GENERAL ROBINSON MODEL R44 II SECTION 1 GENERAL ISSUED: 3 OCT 2002 1-5 DESCRIPTIVE DATA (cont’d) POWERPLANT Model: Lycoming I0-540-AE1A5 Type: Six cylinder, horizontally opposed, direct drive, air cooled, fuel injected, normally aspirated Displacement: 541.5 cubic inches Maximum continuous rating: 205 BHP at 2718 RPM (102% on tachometer) 5 Minute takeoff rating: 245 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 II 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. V ne Never-Exceed Airspeed. V y Speed for best rate of climb. V h 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 II). Critical Altitude Altitude at which full throttle produces maximum allowable power (MCP or TOP). TOGW Takeoff Gross Weight. ROBINSON MODEL R44 II SECTION 1 GENERAL ISSUED: 5 OCT 2011 1-7 PERFORMANCE DEFINITIONS (cont’d) OAT Outside 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 II. 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 II 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 II SECTION 2 LIMITATIONS CONTENTS SECTION 2 LIMIT A TIO NS Page General ................................. 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: 3 OCT 2002 2-i INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 2 LIMITATIONS 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 II. 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. FAA APPROVED: 21 FEB 2014 2-1 ROBINSON MODEL R44 II 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 below 101% permitted for emergency procedures training. POWERPLANT LIMITATIONS ENGINE One Lycoming Model IO-540-AE1A5 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. ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 21 FEB 2014 2-3 WEIGHT LIMITS Maximum gross weight 2500 lb (1134 kg) Minimum gross weight 1600 lb (726 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.) ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 21 FEB 2014 2-4 CENTER OF GRAVITY LIMITS ROBINSON MODEL R44 II SECTION 2 LIMITATIONS REVISED: 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 pullup 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 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 II 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 B95/130 Amber GOST 1012-72 Russian National Standard 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. ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 21 OCT 2016 2-7 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% ENGINE TACHOMETER Lower red line 101% Green arc 101 to 102% Upper red line 102% 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) ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 21 OCT 2016 2-8 INSTRUMENT MARKINGS (cont’d) CYLINDER HEAD TEMPERATURE Green arc 200 to 500°F (93 to 260°C) Red line 500°F (260°C) MANIFOLD PRESSURE Green arc 15.0 to 23.3 in. Hg Yellow arc 19.1 to 26.1 in. Hg Red line 26.1 in. Hg Yellow arc denotes variable MAP limits. See placard on page 2-9. ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 3 OCT 2002 2-9 PLACARDS In clear view and readable by pilot in flight: ROBINSON MODEL R44 II 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 100LL 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 100LL 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 II SECTION 2 LIMITATIONS 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 In clear view of all occupants: NO SMOKING ROBINSON MODEL R44 II SECTION 2 LIMITATIONS FAA APPROVED: 21 FEB 2014 2-12 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 II ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 11 MAY 2020 3-i 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 II 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 V ne 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. 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. ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-2 ROBINSON MODEL R4411 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 GUDE 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 1 500 feet AGL CAUTION Increase rotor RPM to 97% minimum when auto rotating below 500 feet AGL. AIR REST ART PROCEDURE CAUTION Do not attempt restart if engine malfunction is suspected or before safe autorotation is established. Air restarts not recommended below 2000 feet AGL. 1. Mixture - Off. 2. Throttle - Closed. 3. Starter - Engage. 4. Mixture - Move slowly rich while cranking. FAA APPROVED: 3 OCT 2002 3-3 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 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-4 ROBINSON MODEL R44 II 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 II 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. 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 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 7 MAY 2019 3-7 FAA APPROVED: 3 OCT 2002 3-8 ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES 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 engine compartment. 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 rotor gearbox must be refilled with new oil). Hover for at least 30 minutes. If chip light comes on again, replace gearbox before further flight. FAA APPROVED: 17 NOV 2021 3-9 ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES WARNING/CAUTION LIGHTS (cont’d) LOW FUEL Indicates approximately three gallons of usable fuel remaining. The engine will run out of fuel after ten minutes at cruise power. CAUTION Do not use LOW FUEL as a working indication of fuel quantity. AUX FUEL PUMP Indicates low auxiliary fuel pump pressure. If no other indication of a problem, land as soon as practical. If light is accompanied by erratic engine operation, land immediately. FUEL FILTER Indicates fuel strainer contamination. If no other indication of a problem, land as soon as practical. If light is accompanied by aux fuel pump warning light or erratic engine operation, land immediately. CLUTCH Indicates clutch actuator circuit is on, either engaging or disengaging clutch. When switch is in the ENGAGE position, light stays on until belts are properly tensioned. Never take off before light goes out. NOTE Clutch light may come on momentarily during run-ups or during flight to retension belts as they warm-up and stretch slightly. This is normal. If, however, the light flickers or comes on in flight and does not go out within 10 seconds, pull CLUTCH circuit breaker and land as soon as practical. Reduce power and land immediately if there are other indications of drive system failure (be prepared to enter autorotation). Have drive system inspected for a possible malfunction. FAA APPROVED: 11 MAY 2020 3-10 WARNING/CAUTION LIGHTS (cont’d) ALT Indicates low voltage and possible alternator failure. Turn off nonessential electrical equipment and switch ALT off then back on after one second to reset alternator control unit. If light stays on, land as soon as practical. Continued flight without functioning alternator can result in loss of power to tachometers, producing a hazardous flight condition. STARTER ON Indicates starter motor is engaged. If light does not go out when starter button is released, immediately pull mixture off and turn battery switch off. Have starter motor serviced. LOW RPM Indicates rotor speed below 97% RPM. To restore RPM, immediately lower collective, roll throttle on and, in forward flight, apply aft cyclic. Light is disabled when collective is full down. GOV OFF Indicates engine RPM governor is switched off. CARBON MONOXIDE Indicates elevated levels of carbon monoxide (CO) in cabin. Shut off heater and open nose and door vents. If hovering, land or transition to forward flight. If symptoms of CO poisoning (headache, drowsiness, dizziness) accompany light, land immediately. BRAKE Indicates rotor brake is engaged. Release immediately in flight or before starting engine. FULL THROTTLE (if installed) Indicates engine near full throttle. The governor will be ineffective because it cannot increase throttle to maintain RPM. Lower collective as required to extinguish light. HYD (if installed) Indicates hydraulic system is switched off. ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 11 MAY 2020 3-11 AUDIO ALERTS LOW RPM HORN Horn is provided by one or two speakers in the side of the instrument console on earlier aircraft or through the audio system on later aircraft. The horn activates simultaneously with the LOW RPM caution light and indicates rotor speed below 97% RPM. To restore RPM, lower collective, roll throttle on and, in forward flight, apply aft cyclic. Horn and light are disabled when collective is full down. HIGH RPM WARBLE On later aircraft, a warble (high/low tone) in the audio system indicates rotor speed is approaching the 108% RPM limit. Raise collective as required to control RPM. ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-i SECTION 4 NORMAL PROCEDURES CONTENTS Page Recommended Airspeeds . . . . . . . . . . . . . . . . . . . . . . . 4-1 Daily or Preflight Checks . . . . . . . . . . . . . . . . . . . . . . . . 4-1 Before Starting Engine . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 Engine Starting Tips . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-7 Starting Engine and Run-Up . . . . . . . . . . . . . . . . . . . . . . 4-7 Takeoff Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Doors-Off Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10 Practice Autorotation – Power Recovery . . . . . . . . . . . . 4-11 Practice Autorotation – With Ground Contact . . . . . . . . 4-12 Hydraulics-Off Training . . . . . . . . . . . . . . . . . . . . . . . . . 4-12 Descent, Approach, and Landing . . . . . . . . . . . . . . . . . . 4-13 Shutdown Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14 Noise Abatement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-15 INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2018 4-1 SECTION 4 NORMAL PROCEDURES RECOMMENDED AIRSPEEDS Takeoff and Climb 60 KIAS Maximum Rate of Climb (VY ) 55 KIAS Maximum Range 100 KIAS* Maximum Cruise 110 KIAS* (Do not exceed except in smooth air, and then only with caution) Significant Turbulence 60 to 70 KIAS Landing Approach 60 KIAS Autorotation 60 to 70 KIAS* * Certain conditions may require lower airspeed. See Vne placard in Section 2. DAILY OR PREFLIGHT CHECKS Remove ground handling wheels and all covers and tiedowns. Remove even small accumulations of frost, ice, or snow, especially from rotor blades. Check maintenance records to verify aircraft is airworthy. An 8-foot step ladder is recommended for preflight inspection of the main rotor; however, main rotor hub may be reached by first opening right rear seat and stepping on seat support and then stepping on deck below the aux fuel tank. Check general condition of aircraft and verify no visible damage, fluid leakage, or abnormal wear. Verify no fretting at rivets and seams where parts are joined together. Fretting of aluminum parts produces a fine black powder while fretting of steel parts produces a reddish-brown or black residue. Verify Telatemps show no temperature increase that cannot be attributed to a change in operating conditions (mechanics draw a reference line to the right of the highest temperature square which has darkened in operation). Verify torque stripes on critical fasteners are not broken or missing. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2018 4-2 DAILY OR PREFLIGHT CHECKS (cont’d) 1. Upper Forward Cowl Doors – Right Side Battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Oil pressure, alt, aux fuel pump lights . . . . . . . . . . ON Warning light test switches . . . . . . . . . . . Push to test Fuel quantity . . . . . . . . . . . . . . . . . . . . . Check gages Battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Aux fuel tank quantity . . . . . . . . . . . . . . . . . . . Check Fuel filler cap . . . . . . . . . . . . . . . . . . . . . . . . . . . Tight Aux fuel tank . . . . . . . . . . . . . . . . . . . . . . . . No leaks Fuel lines . . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Fuel tank sump, gascolator drains . . . . . . . . . . Sample Gearbox oil . . . . . . . . . . . . . . . . . . . . . . Full, no leaks Hydraulic system . . . . . . . . . . . . . . Fluid full, no leaks Rotor brake . . . . . . . . . . . . . . . . . . . Actuation normal Flex coupling . . . . . . . . . . . . . No cracks, nuts secure Yoke flanges . . . . . . . . . . . . . . . . . . . . . . . No cracks Gearbox, hydraulic pump Telatemps . . . . . . . . Normal Control rod ends . . . . . . . . . . . . Free without looseness Steel tube frame . . . . . . . . . . . . . . . . . . . . . No cracks All fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Tail rotor control . . . . . . . . . . . . . . . . . No interference 2. Main Rotor CAUTION Do not pull down on blades to teeter rotor. To lower a blade, push up on opposite blade. Blades . . . . . . . . . . . . . .Clean and no damage/cracks CAUTION Verify erosion on lower surface of blades has not exposed skin-to-spar bond line. Reference Rotor Systems description in Section 7. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 17 NOV 2021 4-3 DAILY OR PREFLIGHT CHECKS (cont’d) 2. Main Rotor (cont’d) Pitch change boots . . . . . . . . . . . . . . . . . . . . No leaks Main hinge bolts . . . . . . . . . . . . . Cotter pins installed All rod ends . . . . . . . . . . . . . . . Free without looseness All fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Swashplate scissors . . . . . . . . No excessive looseness Upper forward cowl doors . . . . . . . . . . . . . . . Latched 3. Lower Cowl Door – Right Side Air box and duct . . . . . . . . . . . . . . . . . . . . . . . Secure Engine sheet metal . . . . . . . . . . . . . . . . . . . No cracks Fuel lines . . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Oil lines . . . . . . . . . . . . . . . . . . . . No leaks or chafing Exhaust system . . . . . . . . . . . . . . . . . . . . . No cracks Throttle linkage . . . . . . . . . . . . . . . . . . . . . . Operable Cowl door . . . . . . . . . . . . . . . . . . . . . . . . . . . Latched 4. Aft Cowl Door – Right Side Oil cooler door . . . . . . . . . . . . . . . . . . . . . . . . . Check V-belt condition . . . . . . . . . . . . . . . . . . . . . . . . Check V-belt slack . . . . . . . . . 1.5 inches (4 cm) maximum Sprag clutch . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Upper bearing . . . . . . . . . . . . . . . . . . . . . . . . No leaks Telatemp – upper bearing . . . . . . . . . . . . . . . . Normal Sheave condition . . . . . . . . . . . . . . . . . . . . . . . Check Flex coupling . . . . . . . . . . . . . No cracks, nuts secure Yoke flanges . . . . . . . . . . . . . . . . . . . . . . . No cracks Steel tube frame . . . . . . . . . . . . . . . . . . . . . No cracks Tail rotor control . . . . . . . . . . . . . . . . . No interference Tailcone attachment bolts . . . . . . . . . . . . . . . . Check Cowl door . . . . . . . . . . . . . . . . . . . . . . . . . . . Latched 5. Engine Rear Cooling fan nut . . . . . . . . . . . . . Pin in line with marks Cooling fan . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Fan scroll . . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Tailpipe hanger . . . . . . . . . . . . . . . . . . . . . . No cracks ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2018 4-4 DAILY OR PREFLIGHT CHECKS (cont’d) 6. Empennage Tail surfaces . . . . . . . . . . . . . . . . . . . . . . . No cracks Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Position light . . . . . . . . . . . . . . . . . . . . . . . . . . Check Tail rotor guard . . . . . . . . . . . . . . . . . . . . . . No cracks 7. Tail Rotor Gearbox Telatemp . . . . . . . . . . . . . . . . . . . . . Normal Gearbox . . . . . . . . . . . . . . . . . . . . Oil visible, no leaks Blades . . . . . . . . . . . . . . Clean and no damage/cracks Pitch links . . . . . . . . . . . . . . . . . . . . . . . No looseness Teeter bearings . . . . . . . . . . . . . . . . . Check condition Teeter bearing bolt . . . . . . . . . . . . . . . Does not rotate Control bellcrank . . . . . . . . . . . Free without looseness 8. Tailcone Skins . . . . . . . . . . . . . . . . . . . . . . No cracks or dents Strobe light condition . . . . . . . . . . . . . . . . . . . . Check Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check 9. Cowl Door – Left Side Engine oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-9 qts Oil filter . . . . . . . . . . . . . . . . . . . . . . Secure, no leaks Battery and relay (if located here) . . . . . . . . . . Secure Steel tube frame . . . . . . . . . . . . . . . . . . . . . No cracks Engine sheet metal . . . . . . . . . . . . . . . . . . . No cracks Exhaust system . . . . . . . . . . . . . . . . . . . . . No cracks Cowl door . . . . . . . . . . . . . . . . . . . . . . . . . . . Latched 10. Main Fuel Tank Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Filler cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tight Leakage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . None ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2018 4-5 DAILY OR PREFLIGHT CHECKS (cont’d) 11. Fuselage Left Side Baggage compartments . . . . . . . . . . . . . . . . . . Check Removable controls . . . . . . . . . . . . . Secure if installed Collective controls . . . . . . . . . . . . . . . . . . . . . . . Clear Seat belts . . . . . . . . . . . Check condition and fastened Doors . . . . . . . . . . . . . . . . . . . . Unlocked and latched Door hinge safety pins . . . . . . . . . . . . . . . . . Installed Landing gear . . . . . . . . . . . . . . . . . . . . . . . . . . Check Position light . . . . . . . . . . . . . . . . . . . . . . . . . . Check Static port . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear 12. Nose Section Pitot tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Windshield condition and cleanliness . . . . . . . . Check Landing lights . . . . . . . . . . . . . . . . . . . . . . . . . Check Yaw string . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check 13. Fuselage Right Side Baggage compartments . . . . . . . . . . . . . . . . . . Check Seat belts . . . . . . . . . . . Check condition and fastened Aft door . . . . . . . . . . . . . . . . . . Unlocked and latched Door hinge safety pins . . . . . . . . . . . . . . . . . Installed Landing gear . . . . . . . . . . . . . . . . . . . . . . . . . . Check Position light . . . . . . . . . . . . . . . . . . . . . . . . . . Check Static port . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear 14. Cabin Interior Loose articles . . . . . . . . . . . . . . . Removed or stowed Instruments, switches, and controls . . Check condition Clock . . . . . . . . . . . . . . . . . . . . . . . . . . . . Functioning Adjustable pedals . . . . . . . . . . . . . . . . . . . Pins secure CAUTION Remove left seat controls if person in that seat is not a rated helicopter pilot. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 FEB 2014 4-6 DAILY OR PREFLIGHT CHECKS (cont’d) CAUTION Fill baggage compartments under unoccupied seats to capacity before using baggage compartments under occupied seats. Avoid placing objects in compartment which could injure occupant if seat collapses during a hard landing. CAUTION Ensure all doors are unlocked before flight to allow rescue or exit in an emergency. CAUTION Shorter pilots may require cushion to obtain full travel of all controls. Verify aft cyclic travel is not restricted. BEFORE STARTING ENGINE Seat belts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fastened Fuel shut-off valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Cyclic, collective, pedals . . . . . . . . . . . . . . . Full travel free Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . Full travel free Collective . . . . . . . . . . . . . . . . . . . . . Full down, friction ON Cyclic . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral, friction ON Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral Rotor brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengaged Circuit breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . In Landing lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Avionics switch (if installed) . . . . . . . . . . . . . . . . . . . . . OFF Clutch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengaged Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Set HYD and governor switches . . . . . . . . . . . . . . . . . . . . . ON ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-7 ENGINE STARTING TIPS Prime 3 to 5 seconds after fuel pump caution light extinguishes. If engine does not fire after 5 to 7 seconds of cranking, repeat priming sequence and reattempt start. If engine fires momentarily but dies before or while moving mixture to rich, pull mixture off, engage starter, and push mixture slowly rich while cranking. If engine fails to start after three attempts, allow starter to cool ten minutes before next attempt. With a hot engine, it may be helpful to cool fuel in lines by running fuel pump for 30 seconds with mixture OFF prior to beginning start procedure (hold key in prime position). STARTING ENGINE AND RUN-UP Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Closed Battery, strobe switches . . . . . . . . . . . . . . . . . . . . . . . . ON Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Mixture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rich Ignition switch . . . . . . . . . . . . . . . . . . . . . Prime, then Both Mixture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pull OFF Starter . . . . . . . . . . . . . . . . . . . . . Engage until engine fires Mixture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Move full rich Mixture guard . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installed Starter-On light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Set engine RPM . . . . . . . . . . . . . . . . . . . . . . . . . 50 to 60% Clutch switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engaged Blades turning . . . . . . . . . . . . . . . . . . . Less than 5 seconds Alternator switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Oil pressure within 30 seconds . . . . . . . . . . 25 psi minimum Avionics, headsets . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Annunciator panel test (if equipped) . . . . . . . . . All lights on Audio alert (if equipped) . . . . . . . . . . . . . . . . . . . . . . . . Test Wait for clutch light out . . . . . . . . . . . . . Circuit breakers in Warm-up RPM . . . . . . . . . . . . . . . . . . . . . . . . . . 60 to 70% Engine gages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Green Mag drop at 75% RPM . . . . . . . . . . . . 7% max in 2 seconds Sprag clutch check . . . . . . . . . . . . . . . . . . . . . Needles split Doors (if installed) . . . . . . . . . . . . . . . . . Closed and latched Limit MAP chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Hydraulic system . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Governor On, increase throttle . . . . . . . . . . RPM 101-102% Warning lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Lift collective slightly, reduce RPM . . . . . Horn/Light at 97% ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 17 NOV 2021 4-8 STARTING ENGINE AND RUN-UP (cont’d) CAUTION For aircraft which provide low RPM horn through the audio system, a headset for each pilot is required to hear the horn. CAUTION On slippery surfaces, be prepared to counter nose-right rotation with left pedal as governor increases RPM. NOTE For hydraulic system check, use small cyclic inputs. With hydraulics OFF, there should be approximately one half inch of freeplay before encountering control stiffness and feedback. With hydraulics ON, controls should be free with no feedback or uncommanded motion. NOTE Idle mixture and speed may require adjustment as conditions vary from sea level standard. Refer to R44 Maintenance Manual for idle adjustment procedure. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-9 TAKEOFF PROCEDURE 1. Verify doors latched, governor and hydraulics ON, and RPM stabilized at 101 to 102%. 2. Clear area. Slowly raise collective until aircraft is light on skids. Reposition cyclic as required for equilibrium, then gently lift aircraft into hover. 3. Check gages in green and note hover MAP. 4. Lower nose, and accelerate to climb speed following profile shown by height-velocity diagram in Section 5. Avoid exceeding two inches MAP above IGE hover power to prevent excessive nose-down attitude. If RPM drops below 101%, lower collective DOORS-OFF OPERATION Maximum airspeed with any door(s) off is 100 KIAS. Warn passengers to secure loose objects and to keep head and arms inside cabin to avoid high velocity airstream. CAUTION Ensure all seat belts are buckled during door- off flight. Rear seat bottoms may lift if not restrained and items in baggage compartments could be blown out. CAUTION Flight with left door(s) removed is not recom- mended. Loose objects exiting left doors may damage tail rotor. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-10 CRUISE 1. Verify RPM in green arc. 2. Set manifold pressure as desired with collective. Observe MAP and airspeed limits. Maximum recommended cruise speed is 110 KIAS. 3. Verify gages in green, warning lights out. CAUTION Do not exceed 110 KIAS except in smooth air, and then only with caution. In turbulence, use lower airspeed. If turbulence is significant or becomes uncomfortable for the pilot, use 60 to 70 KIAS. CAUTION In-flight leaning with engine mixture control is not allowed. Mixture must be full rich during flight. NOTE When loaded near aft CG limit, slight yaw oscil- lation during cruise can be stopped by applying a small amount of left pedal. PRACTICE AUTOROTATION – POWER RECOVERY 1. Lower collective to down stop and reduce throttle as desired for tachometer needle separation. CAUTION To avoid inadvertent engine stoppage, do not chop throttle to simulate a power failure. Always roll throttle off smoothly. Recover immediately if engine is rough or engine RPM continues to drop. NOTE Governor is inactive below 80% engine RPM regardless of governor switch position. NOTE When entering autorotation from above 6000 feet, reduce throttle slightly before lowering collective to prevent engine overspeed. 2. Adjust collective to keep rotor RPM within limits and adjust throttle for tachometer needle separation. 3. Keep airspeed 60 to 70 KIAS. 4. At about 40 feet AGL, begin cyclic flare to reduce rate of descent and forward speed. 5. At about 8 feet AGL, apply forward cyclic to level aircraft and raise collective to control descent. Add throttle if required to keep RPM in green arc. CAUTION Simulated engine failures require prompt lowering of collective to avoid dangerously low rotor RPM. Catastrophic rotor stall could occur if the rotor RPM ever drops below 80% plus 1% per 1000 feet of altitude. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-11 ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-12 PRACTICE AUTOROTATION – WITH GROUND CONTACT If practice autorotations with ground contact are required for demonstration purposes, perform in same manner as power recovery autorotations except: Prior to cyclic flare, roll throttle off into overtravel spring and hold against hard stop until autorotation is complete. (This prevents throttle correlator from adding power when collective is raised.) Always contact ground with skids level and nose straight ahead. NOTE Have landing gear skid shoes inspected frequently when practicing autorotations with ground contact. Rapid wear of skid shoes may occur. HYDRAULICS-OFF TRAINING Hydraulic system failure may be simulated using the cyclic- mounted hydraulic switch. CAUTION With hydraulics switched OFF, controlling helicopter in a hover may be difficult due to control system feedback forces. CAUTION Before switching hydraulics from OFF to ON, relax force on cyclic and collective to avoid over-controlling. DESCENT, APPROACH, AND LANDING 1. Reduce power with collective as desired. Observe airspeed limits. Maximum recommended airspeed is 110 KIAS except in smooth air. CAUTION Do not initiate a descent with forward cyclic. This can produce a low-G condition. Always initiate a descent by lowering collective. 2. Make final approach into wind at lowest practical rate of descent with initial airspeed of 60 KIAS. 3. Reduce airspeed and altitude smoothly to hover. (Be sure rate of descent is less than 300 FPM before airspeed is reduced below 30 KIAS.) 4. From hover, lower collective gradually until ground contact. 5. After initial ground contact, lower collective to full down position. CAUTION When landing on a slope, return cyclic control to neutral before reducing rotor RPM. CAUTION Never leave helicopter flight controls unattended while engine is running. CAUTION Hold throttle closed if passenger is entering or exiting with engine running and left seat collective installed. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-13 ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-14 SHUTDOWN PROCEDURE Collective down, RPM 60–70% . . . . . . . . . . . . Friction ON Cyclic and pedals neutral . . . . . . . . . . . . . . . . . Friction ON CHT drop . . . . . . . . . . . . . . . . . . . . . . . . . . Throttle closed Clutch switch . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengage Wait 30 seconds . . . . . . . . . . . . . . . . . . . . . . . Mixture OFF Wait 30 seconds . . . . . . . . . . . . . . . . . . . Apply rotor brake Clutch light . . . . . . . . . . . . . . . . . . . . . . . . . . . . Extinguishes Avionics, alt, battery, and ignition switches . . . . . . . . . OFF NOTE If ambient temperature is above 100°F (38°C), cool down at 60-70% RPM for at least one minute before reducing to idle. In hot ambient conditions, it may also be helpful to open engine cowl doors while parked if parking period will be less than one hour. NOTE During idle and after engine shutdown, pilot should uncover one ear and listen for unusual noise which may indicate impending failure of a bearing or other component. CAUTION Do not slow rotor by raising collective during shutdown. Blades may flap and strike tailcone. NOTE HYD switch should be left ON for startup and shutdown to reduce possibility of unintentional hydraulics-off liftoff. Switch OFF only for pre-takeoff controls check or hydraulics-off training. NOTE Rotor brake should be left engaged after shutdown to disable starter buttons and reduce possibility of unintentional starter engagement. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 7 MAY 2019 4-15 NOISE ABATEMENT To improve the quality of our environment and to dissuade overly restrictive ordinances against helicopters, it is imperative that every pilot minimize noise irritation to the public. Following are several techniques which should be employed when possible. 1. Avoid flying over outdoor assemblies of people. When this cannot be avoided, fly as high as practical, preferably over 2000 feet AGL. 2. Avoid blade slap. Blade slap generally occurs at airspeeds below 100 KIAS. It can usually be avoided by maintaining 100 KIAS until rate of decent is over 1000 feet per minute, then using a fairly steep approach until airspeed is below 65 KIAS. With the right door vent open, the pilot can easily determine those flight conditions which produce blade slap and develop piloting techniques to eliminate or reduce it. 3. When departing from or approaching a landing site, avoid prolonged flight over noise sensitive areas. Always fly above 500 feet AGL and preferably above 1000 feet AGL. 4. Repetitive noise is far more irritating than a single occurrence. If you must fly over the same area more than once, vary your flight path to not overfly the same buildings each time. 5. When overflying populated areas, look ahead and select the least noise-sensitive route. NOTE Above procedures do not apply where they would conflict with Air Traffic Control clearances or when, in the pilot’s judgment, they would result in an unsafe flight path. INTENTIONALLY BLANK ROBINSON MODEL R4411 General SECTION 5 PERFORMANCE CONTENTS SECTION 5 PERFORMANCE Page 5-1 Demonstrated Operating Temperature . . . . .. . . . . . . 5-1 Airspeed Calibration Curve . . . . . . . . . . . . . . . . . . . 5-2 Density Altitude Chart . . . . . . . . . . . . . . . . . . . . . . 5-3 IGE Hover Ceiling Vs. Gross Weight . . . . . . . . . . . . . 5-4 OGE Hover Ceiling Vs. Gross Weight . . . . . . . . . . . . 5-5 Height-Velocity Diagram ...................... 5-6 Noise Characteristics . . . . . . . . . . . . . . . . . . . . . . . 5-7 FAA APPROVED: 3 OCT 2002 5-i INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 5 PERFORMANCE FAA APPROVED: 17 NOV 2021 5-1 SECTION 5 PERFORMANCE GENERAL IGE hover controllability has been substantiated in 17 knot wind from any direction up to 9800 feet (2990 meters) density altitude. Refer to hover performance charts for allowable gross weight. CAUTION Performance data presented in this section was obtained under ideal conditions. Performance under other conditions may be substantially less. Indicated airspeed (KIAS) shown on charts assumes zero instrument error. DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated to an outside air temperature of 38°C (100°F) at sea level or 23°C (41°F) above ISA at altitude. ROBINSON MODEL R44 II SECTION 5 PERFORMANCE FAA APPROVED: 3 OCT 2002 5-2 AIRSPEED CALIBRATION CURVE ROBINSON MODEL R4411 SECTION 5 PERFORMANCE f-< Iii ~141--,i,,,.:;+-~+-~::+---+,.q--+-~: ""0 gl2.,..._+-..,.._+-~+-,w;..+-~+-+· - X l:ill0t-::of"'--+-::,t"-+-:::"1'---+-::o«""-t-.,...-+--; ~-+"""""-i...,.i Q ::, EC-I 5 8 < ----------------------!>- 6 t-,,''f--t-,,"'t--t-,"+--...,..+-+;ro+-+-.,,,"fi--+..,, -:;_j,_...,""" f-< iIii 4F-+-,,,,<:+-+,,,,.:+-..;,.,,.::+---½:.-'4-~~~..+-+. Q .2......_..__.........__........._...__...._....__ _.____,._.....__.,___.___.,__. •40 -30 -20 -10 0 10 20 30 40 TEMPERATURE, DEGREES C l I I I I I I • I l I I I l I • 1 • 1 , 1 , 1 1 , 1 , 1 • r • , 1 , 1 , 1 , 1 -40 -20 0 20 40 60 80 TEMPERATURE, DEGREES F DENSITY ALTITUDE CHART FAA APPROVED: 3 OCT 2002 I I j I 100 5-3 1- u. 0 0 0 - X LLJ 0 ::, 1- 5<t: LLJ a: ::, fJ) fl) LLJ a: ll. ROBINSON MODEL R44ll SECTION 5 PERFORMANCE IN GROUND EFFECT AT 2 FOOT SKID HEIGHT FULL THROTTLE ZERO WIND GROSS WEIGHT - KG 950 1000 1050 1100 1150 14 ___..,..___,___..,..________._ OAT 7 6 5 ·c - 30 -20 - 10 0 + 10 + 20 + 30 + 40 " ---+-----+-------+-----1-'li"o 2100 2200 2300 2400 2500 GROSS WEIGHT - LB •F - 22 - 4 + 14 + 32 + 50 + 68 + 86 +104 IGE HOVER CEILING VS. GROSS WEIGHT *Hover controllability with 17 knot wind substantiated up to 9800 feet density altitude. FAA APPROVED: 3 OCT 2002 ROBINSON MODEL R44 II SECTION 5 PERFORMANCE 800 OUT OF GROUND EFFECT TAK EOFF POWER OR FULL THROTTLE ZERO WIND GROSS WEIGHT KG 900 1000 llOO 14 ___-,--____...,__....,._--'f__i--_,.....__-,--..._.,. OAT oc OF - 30 - 22 - 20 - 4 12 1--------+-~~.,___,._,~,---1-------1--- - 10 + 14 0 +32 11 1------1---+----~ /0'1,------------ + 10 + 50 ~ + 20 + 68 ~?- 0 + 30 +86 10 1------1---+--/--+_ _..._ _____,_,J! ~"- + 40 +104 (:> 1- u. g 9 0 ..... X 8 w § 7 I- i'.=...J <( 6 w a: :::> (/) fil 5 a: 0. 4 3 2 1 0 1700 1900 2100 GROSS WEIGHT ~ LB 2300 2500 OGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 3 OCT 2002 5-5 ...J (!) <( 1- w w LL ROBINSON MODEL R44 II SECTION 5 PERFORMANCE 700 650 600 550 500 450 400 350 300 250 200 150 100 50 10 -....__ 0 )I. / / I>-. / I/' / / / / / I/ // )< / )< IX )< IX )< X I)< IX I)< IX I)< IX I)< IX I)< IX I)< X I)< IX I)< IX [>< IX I)< IX IX IX IV IV I>< / I/ I/ I/ I/ IX IX X X X I)< I)< IX X IX [X IY I>< DEMONSTRATED CONDITIONS: SMOOTH HARD SURFACE WIND CALM AVOID OPERATION IN SHADED AREAS r,--8500 FT DENSITY ALTITUDE AT 2250 LB ), /\ / >/ /x / / /I x //I'.>. .,-SEA LEVEL AT 2500 LB X V/ l,,A ,I/ X XX 1/.: ~ X x'X' l'x:' / ;x X X IX X ,\ X X X. IX X -"' \ r-;- RECOMMENDED X ,,x x, IX X x~ ;- TAKEOFF PROFILE 'X' X X IX X X )< I/" X xx IX X X>< X xx X X X>< 'X' 'x X X X X )< I X X X IX X X y ~ / - - - - ---:. I?'\. ,1\ IA x, IX. IX IX X. IX X. X IX X. IX. x_ IA 0 10 20 30 40 50 60 70 80 90 100 110 120 130 KIAS HEIGHT - VELOCITY DIAGRAM FAA APPROVED: 3 OCT 2002 5-6 ROBINSON MODEL R44 II SECTION 5 PERFORMANCE FAA APPROVED: 26 JAN 2024 5-7 NOISE CHARACTERISTICS The following noise levels comply with 14 CFR Part 36, Appendix J noise requirements and were obtained from FAA-approved data from actual noise tests. Model: R44 II Engine: Lycoming IO-540-AE1A5 Gross Weight: 2500 lb (1134 Kg) Configuration VH KTAS Flyover Sound Exposure Level dB(A) Earlier Version 109 80.9 Later Version 108 79.3 Notes: Earlier version — Horizontal Stabilizer is mounted adjacent to tail gearbox. Later version — Horizontal Stabilizer is mounted under tailcone forward of tail rotor. These noise levels meet the requirements for a Stage 3 helicopter as defined in 14 CFR Part 36. NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at, into, or out of any airport. THIS PAGE INTENTIONALLY LEFT BLANK. ROBINSON MODEL R44 II SECTION 5 PERFORMANCE FAA APPROVED: 3 OCT 2002 5-8 SECTION 6 WEIGHT AND BALANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1 Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . 6-2 Loading Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4 ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-i INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-1 SECTION 6 WEIGHT AND BALANCE GENERAL The helicopter must be flown only within weight and balance limits specified in Section 2. Loadings outside these limits can result in insufficient control travel for safe operation. The center of gravity may be adjusted by adding removable ballast (any appropriate item of mass) to any under-seat baggage compartment. Recalculate weight and balance after adding ballast, and verify ballast meets baggage compartment limits given in Section 2. Loaded helicopter weight and balance can be determined using the method given under LOADING INSTRUCTIONS. In accordance with FAA procedures, the detail weight and balance data of this section are not subject to FAA approval. The loading instructions of this section, however, have been approved by the FAA as satisfying all requirements for instructions on loading of the rotorcraft within approved limits of weight and center of gravity and on maintaining the loading within such limits. CAUTION Fuel burn causes CG to move forward during flight. Always determine safe loading with empty fuel as well as with takeoff fuel. Payload may be limited by forward CG as fuel is burned. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-2 WEIGHT AND BALANCE RECORD The following form should be used to maintain a continuous record of your helicopter’s weight and balance. Each time an item of equipment is removed or installed, an entry must be made and the new empty CG determined. The original factory weight and balance and an equipment list is supplied with each helicopter on a form which is inserted at the end of this section. This weight and balance provides the first entry in the Weight and Balance Record form. NOTE Calculated CG with full fuel and 150 lb pilot must be within CG limits. Following modification, ad- justment to fixed nose ballast may be required. See R44 Maintenance Manual. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-3 WEIGHT AND BALANCE RECORD (Continuous History of Changes in Structure or Equipment Affecting Weight and Balance) HELICOPTER MODEL R44 II SERIAL NUMBER: DATE DESCRIPTION OF ARTICLE OR MODIFICATION WEIGHT CHANGE RUNNING BASIC EMPTY WEIGHT ADDED (+) REMOVED (—) WEIGHT (lb) LONGITUDINAL LATERAL (+ = RIGHT SIDE) WEIGHT (lb) LONGITUDINAL LATERAL Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) HELICOPTER AS WEIGHED WEIGHT AND BALANCE RECORD (cont’d) ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 26 JAN 2024 6-4 LOADING INSTRUCTIONS The following table may be used when calculating loaded helicopter weight and CG position. COMMON ITEM WEIGHT & CG Item Weight (lb) Longitudinal arm (in.) Lateral arm (in.) (+ = right side) Pilot (right forward seat) 49.5* +12.2 Left forward passenger 49.5* —10.4 Baggage under forward seats 44.0 ±11.5 Aft passengers and baggage under aft seats 79.5 ±12.2 Main fuel** 106.0 —13.5 Aux fuel** 102.0 +13.0 Forward doors 7.5 each 49.4 ±24.0 Aft doors 7.0 each 75.4 ±23.0 Removable controls (cyclic, collective, pedals) 2.0 31.0 —13.0 Items on accessory mount bars 25.0 ±14.0 * If additional backrest cushion is used, subtract thickness of compressed cushion. ** A longitudinal arm of 104.5 in. may be used for combined main and aux fuel. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 26 JAN 2024 6-5 LOADING INSTRUCTIONS (cont’d) The following sample calculation demonstrates how to determine loaded helicopter weight and center of gravity. A worksheet is provided on the page following the sample calculation for a weight and balance calculation for your helicopter. Calculated weight and balance must be compared with the CG limits given in Section 2 to determine safe loading. Both takeoff and empty fuel conditions must be within limits. Lateral CG usually falls well within limits for conventional loadings. If an unusual lateral installation or loading occurs, lateral CG should be checked against the CG limits given in Section 2. The lateral reference datum is the aircraft centerline with items to the right positive and items to the left negative. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 26 JAN 2024 6-6 LOADING INSTRUCTIONS (cont’d) SAMPLE LOADING CALCULATION Item Weight (lb) Location Moment Long. Arm (in.) Lat. Arm (in.) += Right Side Long. (in.-lb) Lat. (in.-lb) Basic empty weight 1510 106.5 0.2 160,815 302 Remove forward right door —7.5 49.4 24.0 —371 —180 Remove forward left door 49.4 —24.0 Remove aft right door 75.4 23.0 Remove aft left door 75.4 —23.0 Remove left seat controls 31.0 —13.0 Pilot (forward right seat) 170 49.5 12.2 8415 2074 Left forward passenger 170 49.5 —10.4 8415 —1768 Aft right passenger 170 79.5 12.2 13,515 2074 Aft left passenger 170 79.5 —12.2 13,515 —2074 Baggage under forward right seat 10 44.0 11.5 440 115 Baggage under forward left seat 10 44.0 —11.5 440 —115 Baggage under aft right seat 79.5 12.2 Baggage under aft left seat 10 79.5 —12.2 795 —122 Items on accessory mount bars 5 25.0 14.0 125 70 Zero usable fuel weight and CG* 2217.5 92.9 0.2 206,104 376 Usable main fuel at 6 lb/gal. 177 106.0 —13.5 18,762 —2390 Usable aux fuel at 6 lb/gal. 102 102.0 13.0 10,404 1326 Takeoff Gross Weight and CG* 2496.5 94.2 —0.3 235,270 —688 * CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE REVISED: 26 JAN 2024 6-7 LOADING INSTRUCTIONS (cont’d) LOADING CALCULATION WORKSHEET Item Weight (lb) Location Moment Long. Arm (in.) Lat. Arm (in.) += Right Side Long. (in.-lb) Lat. (in.-lb) Basic empty weight Remove forward right door 49.4 24.0 Remove forward left door 49.4 —24.0 Remove aft right door 75.4 23.0 Remove aft left door 75.4 —23.0 Remove left seat controls 31.0 —13.0 Pilot (forward right seat) 49.5 12.2 Left forward passenger 49.5 —10.4 Aft right passenger 79.5 12.2 Aft left passenger 79.5 —12.2 Baggage under forward right seat 44.0 11.5 Baggage under forward left seat 44.0 —11.5 Baggage under aft right seat 79.5 12.2 Baggage under aft left seat 79.5 —12.2 Items on accessory mount bars 25.0 Zero usable fuel weight and CG* Usable main fuel at 6 lb/gal. 106.0** —13.5 Usable aux fuel at 6 lb/gal. 102.0** 13.0 Takeoff Gross Weight and CG* * CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ** A longitudinal arm of 104.5 in. may be used for combined main and aux fuel. Do not use combined main and aux fuel if calculating lateral arm. THIS PAGE INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE ISSUED: 21 FEB 2014 6-8 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 17 NOV 2021 7-i SECTION 7 SYSTEMS DESCRIPTION CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1 Rotor Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Drive System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Removable Flight Controls . . . . . . . . . . . . . . . . . . . . . . . 7-5 Control Friction Adjustment . . . . . . . . . . . . . . . . . . . . . . 7-6 RPM Governor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-6 Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-7 Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-8 Clutch Actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-9 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-10 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-12 Lighting System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-17 External Power Receptacle (Optional) . . . . . . . . . . . . . . 7-18 Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18 Audio System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Optional Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Pitot-Static System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-24 Dual Tachometer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-24 Warning and Caution Lights . . . . . . . . . . . . . . . . . . . . . . 7-25 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-26 Engine Monitoring Unit . . . . . . . . . . . . . . . . . . . . . . . . . 7-27 Cabin Heating and Ventilation . . . . . . . . . . . . . . . . . . . . 7-28 Seats, Belts, and Baggage . . . . . . . . . . . . . . . . . . . . . . . 7-28 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-29 Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-30 Carbon Monoxide Detector . . . . . . . . . . . . . . . . . . . . . . 7-31 ADS-B Equipment . . . . . . . . . . . . . . . . . . . . . . . . 7-32 Emergency Locator Transmitter (Optional) . . . . . . . . . . . 7-33 Accessory Mounts (Optional) . . . . . . . . . . . . . . . . . . . . 7-34 Cockpit Camera (Optional) . . . . . . . . . . . . . . . . . . . . . . 7-35 Cyclic Guard (Optional) . . . . . . . . . . . . . . . . . . . . . . . 7-36 INTENTIONALLY BLANK REVISED: 5 MAR 2015 7-1 SECTION 7 SYSTEMS DESCRIPTION GENERAL The R44 II is a four-place, single main rotor, single engine helicopter constructed primarily of metal and equipped with skid-type landing gear. The primary fuselage structure is welded steel tubing and riveted aluminum sheet. The tailcone is a monocoque structure in which aluminum skins carry most primary loads. Fiberglass and thermoplastics are used in secondary cabin structure, engine cooling shrouds, and various other ducts and fairings. The cabin doors are also constructed of fiberglass and thermoplastics. Four right-side cowl doors provide access to the main gearbox, drive system, and engine. A left-side engine cowl door provides access to the engine oil filler and dip stick. Additional access to controls and other components for maintenance is provided by removable panels and cowlings. Stainless steel firewalls are located forward of and above the engine. The four cabin doors are removable. Refer to Section 8 for removal and installation procedures. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 5 MAR 2015 7-2 ROTOR SYSTEMS The main rotor has two all-metal blades mounted to the hub by coning hinges. The hub is mounted to the shaft by a teeter hinge. The coning and teeter hinges use self-lubricated bearings. Droop stops for the main rotor blades provide a teeter hinge friction restraint which normally prevents the rotor from teetering while starting or stopping. Pitch change bearings for each blade are enclosed in a housing at the blade root. The housing is filled with oil and sealed with an elastomeric boot. Each blade has a thick stainless steel spar at the leading edge which is resistant to corrosion and erosion. The skins are bonded to the spar approximately one inch aft of the leading edge. Blades must be refinished if the paint erodes to bare metal at the skin-to-spar bond line. Bond may be damaged if bond line is exposed. The tail rotor has two all-metal blades and a teetering hub with a fixed coning angle. The pitch change bearings have self-lubricated liners. The teeter hinge bearings are elastomeric. The tail rotor blades are constructed with aluminum skins and root fittings. Maintaining the paint finish will reduce corrosion and erosion. DRIVE SYSTEM A vee-belt sheave is bolted directly to the engine output shaft. Vee-belts transmit power to the upper sheave which has an overrunning clutch contained in its hub. The inner shaft of the clutch transmits power forward to the main rotor and aft to the tail rotor. Flexible couplings are located at the main gearbox input and at each end of the long tail rotor drive shaft. The main gearbox contains a single-stage spiral-bevel gear set which is splash lubricated. Cooling ducts under the gearbox are connected to the top of the engine cooling scroll. The main gearbox is supported by four rubber mounts. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 17 NOV 2021 7-3 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION DRIVE SYSTEM (cont’d) The long tail rotor drive shaft has no support bearings but has a lightly-loaded damper bearing. The tail gearbox contains a single 90° splash-lubricated spiral-bevel gear set. POWERPLANT One Lycoming IO-540 six-cylinder, horizontally-opposed, overhead-valve, air-cooled, fuel-injected engine with a wet sump oil system powers the helicopter. The engine is equipped with a starter, alternator, shielded ignition, two magnetos, muffler, two oil coolers, oil filter, and induction air filter. See Sections 1 and 2 for powerplant specifications and limitations. A direct-drive, squirrel-cage fan wheel mounted to the engine output shaft supplies cooling air to the cylinders and oil coolers via a fiberglass and aluminum shroud. Induction air enters through an opening on the right side of the fuselage and passes through the air filter within the air box. Air then passes along a flexible duct, through the fuel control, and into the engine. A spring-loaded door in the air box automatically opens to bypass the filter with engine compartment air should the filter or intake become blocked. The pilot should adhere to recommended procedures in the Lycoming Operator’s Manual to obtain maximum engine life and efficiency. FLIGHT CONTROLS Dual controls are standard equipment and all primary controls are actuated through push-pull tubes and bellcranks. Bearings used throughout the control system are either sealed ball bearings which do not require lubrication or have self-lubricated liners. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 17 NOV 2021 7-4 FLIGHT CONTROLS (cont’d) Flight control operation is conventional. The cyclic is center mounted with the left and right control grips mounted to a cross tube which pivots on the center cyclic post. On later aircraft, the pilot’s cyclic grip angle can be adjusted fore and aft relative to the cross tube by a mechanic to achieve the most comfortable hand position. The most forward position provides the most control clearance at aft cyclic for larger pilots. Pilots should always verify the ability to apply full control travel prior to flight. Collective operation is conventional. The engine throttle is correlated to collective inputs through a mechanical linkage. When the collective is raised, the throttle is opened and when the collective is lowered, the throttle is closed. The collective stick also incorporates a twist grip throttle control which is described in the Engine Controls section. CAUTION Above 6000 feet (1800 meters), throttle- collective correlation and governor are less effective. Therefore, power changes should be slow and smooth. CAUTION At high power settings above 6000 feet (1800 meters), the throttle is frequently wide open and RPM must be controlled with collective. Right-side tail rotor pedals are adjustable. To adjust, remove quick-release pin on each pedal by depressing button and pulling. Slide pedal fore or aft to most comfortable of three adjustment positions and reinstall quick-release pin. Verify pins are secure before flight. Left-side pedals are not adjustable. However, optional pedals designed for shorter pilots (Robinson part nos. F755-9 and -10) may be installed in place of standard pedals. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-5 REMOVABLE FLIGHT CONTROLS Left seat pilot controls may be removed and installed by maintenance personnel or pilots as follows: 1. To remove cyclic grip, remove quick-release pin by depressing button and pulling, then pull outward on left grip while supporting cyclic center post. Rotate right- side cyclic cross tube clockwise to stop, depress stop pin under cyclic pivot, and continue clockwise rotation one turn to wind up balance spring. To install removable cyclic grip, use reverse procedure. NOTE Later aircraft have a knurled ring next to the quick-release pin which may be hand tightened to eliminate freeplay. The ring must be loose (rotate counterclockwise looking inboard) to remove pin. CAUTION Overrotating cyclic cross tube in either wound or unwound direction will damage balance spring. CAUTION After removing cyclic grip, place plastic cap on exposed cyclic cross tube to prevent possible injury to left seat passenger. 2. To remove collective, push boot aft to expose locking pins. Depress locking pins and pull forward on stick. To install, use reverse procedure. It may be necessary to rotate stick slightly to allow pins to snap into place. CAUTION When collective is installed, ensure that both locking pins are fully engaged through holes on each side. 3. To remove tail rotor pedals, depress locking pin while twisting pedal counterclockwise, then pull up. To install, use reverse procedure. On later aircraft, a cover which is stowed under the floor scuff plate may be rotated up to cover the floor openings when the pedals are removed. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-6 CONTROL FRICTION ADJUSTMENT Cyclic and collective controls are equipped with adjustable friction devices. The collective friction lever is located near the aft end of the pilot’s collective. It is actuated aft to increase friction and forward to release it. The cyclic friction knob is located left of the cyclic center post. Turning the knob clockwise applies friction to both longitudinal and lateral cyclic. CAUTION Control friction must be used with caution during flight. Excessive friction may make the helicopter difficult to control. The pedals actuate push-pull controls connected directly to the tail rotor pitch control and do not incorporate any friction devices. An elastomeric trim spring provides a left pedal force to balance feedback forces in flight. RPM GOVERNOR The governor maintains engine RPM by sensing changes and applying corrective throttle inputs through a friction clutch which can be easily overridden by the pilot. The governor is active only above 80% engine RPM and can be switched on or off using the toggle switch on the end of the right seat collective. The governor is designed to assist in controlling RPM under normal conditions. It may not prevent over- or under-speed conditions generated by aggressive flight maneuvers. CAUTION When operating at high density altitudes, governor response rate may be too slow to prevent overspeed during gusts, pull-ups, or when lowering collective. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-7 HYDRAULIC SYSTEM Hydraulically-boosted main rotor flight controls eliminate cyclic and collective feedback forces. The hydraulic system consists of a pump, three servos, a reservoir, and interconnecting lines. The working fluid is MIL-H-5606 and normal operating pressure is 450 to 500 psi. The pump is mounted on and driven by the main gearbox. A servo is connected to each of the three push-pull tubes that support the main rotor swashplate. The reservoir is mounted on the steel tube frame behind the main gearbox and includes a filter, pressure relief valve, and pilot-controlled pressure shut-off valve. A sight gage for pre-flight fluid level checks is incorporated in the reservoir and is visible by opening a right side cowl door. A vented filler cap is located on top of the reservoir. The pressure shut-off valve is solenoid-actuated and controlled by the hydraulic switch on the pilot’s cyclic. The switch should be left ON during helicopter shutdown and start up except during the hydraulic system check. NOTE Electrical power is required to switch hydraulics OFF. Pulling HYD circuit breaker will NOT turn off hydraulics but will disable hydraulic switch. Without hydraulic pressure, a large pilot input force is required to increase collective. Collective inputs also cause longitudinal cyclic forces which makes it difficult to maintain a steady hover. The servos have an irreversible feature to prevent rotor feedback forces from moving the controls. This allows the pilot to relax pressure on the controls in steady cruise flight. However, any cyclic input will cause the collective to lower and therefore the collective will have to be increased periodically. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-8 ENGINE CONTROLS A twist-grip throttle control is located on each collective stick. The controls are interconnected and actuate the throttle valve through a mechanical linkage. The engine throttle is also correlated to collective inputs through a mechanical linkage. When the collective is raised, the throttle is opened and when the collective is lowered, the throttle is closed. The electronic engine governor makes minor throttle adjustments by rotating the twist grip to maintain RPM within power-on limits. Manual manipulation of the twist grip is not typically required except during start up, shut down, autorotation practice, and emergencies. An overtravel spring located in the throttle linkage allows the pilot to roll throttle off beyond the idle stop prior to a ground contact (run-on) autorotation landing. This prevents the throttle from opening when the collective is raised. Correct throttle linkage adjustment may be verified during preflight by rolling the twist-grip through the overtravel spring and holding against the hard idle stop. The fuel control throttle arm should just barely start to move when the collective is raised full up. Other engine controls include a mixture control on the console face, push-to-start buttons on pilot’s cyclic and collective, an engine governor switch on pilot’s collective, and a key-type ignition switch. The cyclic start button allows the pilot to maintain cyclic control during an air restart. The momentary (most clockwise) ignition switch position operates the auxiliary fuel pump for engine priming. CAUTION Starter buttons are active when master switch is on, even if ignition switch is off. Rotor brake should be left engaged after shutdown to disable starter button and reduce possibility of unintentional starter engagement. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-9 CLUTCH ACTUATOR After the engine is started, it is coupled to the rotor drive system through vee-belts which are tensioned by raising the upper drive sheave. An electric actuator, located between the drive sheaves, raises the upper sheave when the pilot engages the clutch switch. The actuator senses compressive load (belt tension) and switches off when the vee-belts are properly tensioned. The clutch caution light illuminates whenever the actuator circuit is energized, either engaging, disengaging, or retensioning the belts. The light stays on until the belts are properly tensioned or completely disengaged. Belt slack during engine start should be adjusted such that blades begin turning within five seconds of clutch engagement. Excessive slack may cause belts to jump out of sheave grooves during start. Periodic readjustment by a mechanic may be required as belts wear in service. A fuse located on the test switch panel prevents an actuator motor overload from tripping the clutch circuit breaker. If the fuse blows, the actuator motor will stop but the clutch caution light will remain illuminated. An open circuit breaker removes power from both the motor and the light. With an open circuit breaker, no belt tensioning will occur, and the light will not function to indicate an abnormal condition. CAUTION Never take off while clutch caution light is on. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-10 FUEL SYSTEM The fuel system includes main and auxiliary tanks, a shutoff valve control located between the front seats, a strainer (gascolator), an engine-driven pump, and an auxiliary (electric) pump. The fuel tanks have flexible bladders in aluminum enclosures. Fuel tank air vents are located inside the mast fairing. A fuel return line allows pump supply in excess of engine demand to return to the fuel tanks. The auxiliary pump primes the engine for starting and runs in flight to provide fuel pump redundancy. The engine will function normally with either the engine-driven or auxiliary (electric) pump operating. The ignition switch prime (momentary) position operates the auxiliary fuel pump for priming prior to engine start. After start, the pump runs continuously as long as the engine has oil pressure and the clutch switch is in the engage position. A pressure switch on the gascolator illuminates the fuel filter caution light if the strainer becomes contaminated. Continued operation with an illuminated filter caution light may result in fuel starvation. A pressure switch downstream of the auxiliary fuel pump illuminates the aux fuel pump caution light if auxiliary pump output pressure is low. When the clutch switch is disengaged, the auxiliary pump is off and the aux fuel pump caution light should be illuminated. Proper mechanical fuel pump function is indicated by normal engine operation after engine start prior to clutch switch engagement and before shutdown while clutch switch is disengaged. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-11 FUEL SYSTEM (cont’d) Plunger-style drain valves are provided for the gascolator and for each fuel tank sump. The gascolator is located on the lower right side of the firewall and is drained by pushing up on the plastic tube which extends below the belly. Valves for both tanks are located inside the right cowl door below the auxiliary tank. Fuel samples are taken by extending the plastic tubes clear of the aircraft and pushing on the plungers. On newer helicopters, a glass tube stowed inside the upper, aft cowl door is provided which may be used to catch the fuel samples. Fuel should be sampled from all three locations prior to the first flight of the day and after refueling to verify no contamination and correct grade. The fuel gages are electrically operated by float-type transmitters in the tanks. When the gages read E the tanks are empty except for a small quantity of unusable fuel. The low fuel caution light is actuated by a separate electric sender located on the bottom of the main tank. The auxiliary tank is interconnected with the main tank and is located somewhat higher so it will become empty first while fuel still remains in the main tank. The fuel shutoff valve controls flow from both tanks to the engine. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 17 NOV 2021 7-12 ELECTRICAL SYSTEM A 28-volt DC electrical system which includes an alternator and a sealed lead-acid battery is standard. The battery is located either in the engine compartment, under the left front seat, or beneath the instrument console. The circuit breaker panel is on the ledge just forward of the left front seat. Breakers are marked to indicate function and amperage. Inflight reset of circuit breakers is not recommended. The battery switch controls the battery relay which disconnects the battery from the electrical system. A wire protected by a fuse near the battery bypasses the battery relay to allow both tachometers and the clock to continue to receive battery power with the battery switch off. The alternator control unit protects the electrical system from overvoltage conditions. The ammeter indicates current to the battery (“—” indicates discharge). An ALT caution light or ammeter discharge indication in flight indicates low voltage and possible alternator failure. Turn off nonessential electrical equipment and switch alternator off then back on after one second to reset alternator control unit. If ALT light stays on or ammeter still indicates discharge, land as soon as practical. CAUTION Continued flight without functioning alterna- tor can result in loss of power to tachome- ters, producing a hazardous flight condition. NOTE Except for emergency procedures, do not operate alternator with battery switched off. The battery helps protect electrical equip- ment from voltage spikes. Later aircraft have an avionics master switch which controls power to the avionics bus. This allows all avionics to be switched on and off by a single switch. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-13 ELECTRICAL SYSTEM (EARLIER AIRCRAFT) ELECTRICAL SYSTEM (cont’d) BATT ERY RE LA Y BYPA SS CIR CU IT BATTER Y SW IT CH CYC LI C J L COLL ECTIV E START BUTT ON7 _....__ , START BUTT ON INTERCO M SYST EM .,_.::..::..::..:..:::~;&..~ GOV ER NOR HYDRAU LI CISO LENOID LT MA P LI GHT REVISED: 17 NOV 2021 7-14 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM (cont’d) ELECTRICAL SYSTEM (LATER AIRCRAFT) REVISED: 21 FEB 2014 7-15 CIRCUIT BREAKER PANEL – TYPICAL (EARLIER AIRCRAFT) ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM (cont’d) REVISED: 21 FEB 2014 7-16 CIRCUIT BREAKER PANEL – TYPICAL (LATER AIRCRAFT) ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM (cont’d) ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-17 LIGHTING SYSTEM A red anti-collision light is installed on the tailcone and is controlled by the strobe switch. Position lights are installed on each side of the cabin and in the tail and are controlled by the nav lights switch. Post and internal lights (earlier aircraft) or a light at the top of the windshield (later aircraft) illuminate the instruments. Instrument lighting is active when the nav lights switch is on and lighting is dimmed via the knob above the nav lights switch. An overhead map light mounted on a swivel is controlled by an adjacent switch. The map light may be used for emergency lighting of the instrument panel. Two landing lights are installed in the nose at different vertical angles to increase the lighted area. One landing light switch controls both lights and is located on the cyclic center post. NOTE Landing lights operate only when clutch actuator switch is in the engage position. NOTE Continuous operation of landing and position lights in flight is recommended to promote collision avoidance. An optional flashing light may be mounted on the tailcone in addition to the standard anti-collision light. On earlier aircraft, the optional light is controlled by the strobe switch and the standard light is powered whenever the battery switch is on. On later aircraft, the optional light is controlled by a separate switch. REVISED: 26 JAN 2024 7-18 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION EXTERNAL POWER RECEPTACLE (OPTIONAL) An optional 28-volt SAE AS35061-style external power receptacle is located inside the right engine cowl door. When the battery is switched on, the external power relay and the battery relay both close, connecting external power to the aircraft electri