R44 II Pilot’s Operating Handbook

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 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 2018 2-2 ROTOR SPEED LIMITS TACHOMETER READING ACTUAL RPM Power On Maximum Minimum* 102% 101% 408 404 Power Off Maximum Minimum 108% 90% 432 360 *Transient operation below 101% permitted for emergency procedures training. POWERPLANT LIMITATIONS ENGINE One Lycoming Model IO-540-AE1A5 OPERATING LIMITS Engine Maximum Speed 2718 RPM (102%) 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. 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 FAA APPROVED: 7 MAY 2018 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 right 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. 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 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 7 MAY 2018 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 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 Low RPM Horn & Caution Light . . . . . . . . . . . . . . . . . . . 3-10 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 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: 21 OCT 2016 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. 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 warning horn are on separate 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: 21 FEB 2014 3-7 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. BRAKE Indicates rotor brake is engaged. Release immediately in flight or before starting engine. 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. GOV-OFF Indicates engine RPM throttle governor is 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. 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. LOW RPM HORN & CAUTION LIGHT A horn and an illuminated caution light indicate that rotor RPM may be below safe limits. To restore RPM, immediately roll throttle on, lower collective and, in forward flight, apply aft cyclic. The horn and caution light are disabled when collective is full down. ROBINSON MODEL R44 II SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-10 ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 OCT 2016 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Doors-Off Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Practice Autorotation – Power Recovery . . . . . . . . . . . . 4-10 Practice Autorotation – With Ground Contact . . . . . . . . 4-11 Hydraulics-Off Training . . . . . . . . . . . . . . . . . . . . . . . . . 4-11 Descent, Approach, and Landing . . . . . . . . . . . . . . . . . . 4-12 Shutdown Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13 Noise Abatement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14 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: 7 MAY 2018 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . Check 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: 21 FEB 2014 4-7 ENGINE STARTING TIPS During prime, aux fuel pump warning light may remain illuminated momentarily. Continue prime 3 to 5 seconds after light extinguishes. If engine does not fire after 5 to 7 seconds of cranking, repeat priming sequence and reattempt start. If engine fails to start after three attempts, allow starter to cool ten minutes before next attempt. 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. 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 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 . . . . . . . . . . . . . . . . . . . . . . . . . . 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 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 OCT 2016 4-9 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. 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: 10 JUL 2012 4-10 PRACTICE AUTOROTATION - POWER RECOVERY 1. Lower collective to down stop and adjust throttle as required for small tachometer needle separation. CAUTION To avoid inadvertent engine stoppage, do not roll throttle to full idle. Roll throttle off smoothly only enough for a small visible needle split. 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 in green arc and adjust throttle for small 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. 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 overcontrolling. ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 10 JUL 2012 4-11 ROBINSON MODEL R44 II SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 OCT 2016 4-12 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 knots. 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: 21 FEB 2014 4-13 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 CAUTION Do not slow rotor by raising collective during shutdown. Blades may flap and strike tailcone. 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. 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. 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 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: 21 FEB 2014 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 cyclic 0.6 35.8 —8.0 Removable collective 0.8 47.0 —21.0 Removable pedals (both pedals) 0.8 16.8 —9.5 * 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: 21 FEB 2014 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. These may 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: 21 FEB 2014 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 cyclic 35.8 —8.0 Remove collective 47.0 —21.0 Remove pedals (both) 16.8 —9.5 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 Zero usable fuel weight and CG* 2212.5 93.1 0.1 205,979 306 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* 2491.5 94.4 —0.3 235,145 —758 * CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ROBINSON MODEL R44 II SECTION 6 WEIGHT AND BALANCE ISSUED: 21 FEB 2014 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 cyclic 35.8 —8.0 Remove collective 47.0 —21.0 Remove pedals (both) 16.8 —9.5 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 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: 21 OCT 2016 7-i SECTION 7 SYSTEMS DESCRIPTION CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1 Rotor Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Drive System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-4 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 Cabin Heating and Ventilation . . . . . . . . . . . . . . . . . . . . 7-26 Seats, Belts, and Baggage . . . . . . . . . . . . . . . . . . . . . . . 7-26 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-27 Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-28 Carbon Monoxide Detector . . . . . . . . . . . . . . . . . . . . . . 7-29 Emergency Locator Transmitter (Optional) . . . . . . . . . . . 7-30 Optional Accessory Mounts . . . . . . . . . . . . . . . . . . . . . . 7-31 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 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-4 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. 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, throttle-collective correla- tion and governor are less effective. There- fore, power changes should be slow and smooth. CAUTION At high power settings above 6000 feet, 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. 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: 21 FEB 2014 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 and are of the push-to-reset type. 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) REVISED: 21 FEB 2014 7-14 ELECTRICAL SYSTEM (LATER AIRCRAFT) ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM (cont’d) 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: 18 DEC 2015 7-18 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION EXTERNAL POWER RECEPTACLE (OPTIONAL) An optional 28-volt MS3506-compatible 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 electrical system and battery. The external power relay will not close if reverse polarity is sensed by the receptacle. A separate wire from the external power receptacle to the battery bypasses the external power and battery relays. This wire allows battery charging via the external receptacle with the battery switch off. A 10-amp circuit breaker at the receptacle opens if current exceeds normal charging levels, and a diode provides polarity protection. To use ground power for engine starting, have ground personnel connect ground power to the external receptacle prior to engaging starter, disconnect after engine start, and latch cowl door. Starts using ground power assist follow the same procedure as normal starts. INSTRUMENT PANEL Standard primary instruments include an airspeed indicator, engine and rotor dual tachometer, altimeter, manifold pressure gage, and magnetic compass. Engine gages include an ammeter, oil pressure, oil temperature, cylinder head temperature, and fuel quantity for main and aux tanks. Also standard are a clock, a digital outside air temperature gage, and a collective-activated hourmeter which may be used for recording time in service. Views of typical instrument panels are given on the following pages. Pilots should familiarize themselves with panel layout and equipment installations for each specific aircraft that they fly. For instrument panels with electronic flight displays, a P/N D327 light filter may be used to reduce reflections in the windshield at night. The light filter is installed by clipping it to the front of the display. Filter use is at pilot discretion. REVISED: 21 FEB 2014 7-19 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION 1. VERTICAL SPEED INDICATOR 21. GOVERNOR-OFF LIGHT 2. OPTIONAL INSTRUMENT 22. HOURMETER 3. AIRSPEED INDICATOR 23. CLOCK 4. ENGINE AND ROTOR TACHS 24. ENGINE INSTRUMENTS 5. ALTIMETER 25. PANEL LIGHTS DIMMER 6. OPTIONAL INSTRUMENT 26. ROTOR BRAKE LIGHT 7. MANIFOLD PRESSURE GAGE 27. NAVIGATION LIGHTS SWITCH 8. CLUTCH ACTUATOR LIGHT 28. STROBE LIGHT SWITCH 9. M.R. GEARBOX TEMP LIGHT 29. CLUTCH ACTUATOR SWITCH 10. M.R. GEARBOX CHIP LIGHT 30. ALTERNATOR SWITCH 11. CARBON MONOXIDE LIGHT 31. BATTERY SWITCH 12. STARTER-ON LIGHT 32. IGNITION AND PRIMER SWITCH 13. T.R. GEARBOX CHIP LIGHT 33. CABIN AIR 14. LOW FUEL LIGHT 34. INTERCOM 15. LOW RPM LIGHT 35. MIXTURE CONTROL 16. FUEL FILTER LIGHT 36. OUTSIDE AIR TEMP/VOLTMETER 17. AUX FUEL PUMP LIGHT 37. CYCLIC FRICTION 18. ALT LOW VOLTAGE LIGHT 38. CABIN HEAT 19. ENGINE FIRE LIGHT 39. ELT SWITCH (OPTIONAL) 20. OIL PRESSURE LIGHT 40. HEATED PITOT SWITCH (OPT’L) INSTRUMENT PANEL – TYPICAL (EARLIER AIRCRAFT) (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) REVISED: 21 FEB 2014 7-20 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION 1. ENGINE AND ROTOR TACHS 23. OIL PRESSURE LIGHT 2. AIRSPEED INDICATOR 24. GOVERNOR-OFF LIGHT 3. ARTIFICIAL HORIZON 25. FUEL FILTER LIGHT 4. ALTIMETER 26. HOURMETER 5. MANIFOLD PRESSURE GAGE 27. CLOCK 6. TURN COORDINATOR 28. ENGINE INSTRUMENTS 7. HSI 29. PANEL LIGHTS DIMMER 8. VERTICAL SPEED INDICATOR 30. ROTOR BRAKE LIGHT 9. OPTIONAL INSTRUMENT 31. NAVIGATION LIGHTS SWITCH 10. OPTIONAL INSTRUMENT 32. STROBE LIGHT SWITCH 11. MARKER BEACON 33. CLUTCH ACTUATOR SWITCH 12. M.R. GEARBOX TEMP LIGHT 34. ALTERNATOR SWITCH 13. T.R. GEARBOX CHIP LIGHT 35. BATTERY SWITCH 14. M.R. GEARBOX CHIP LIGHT 36. IGNITION AND PRIMER SWITCH 15. STARTER-ON LIGHT 37. CABIN AIR 16. LOW RPM LIGHT 38. INTERCOM 17. LOW FUEL LIGHT 39. MIXTURE CONTROL 18. CARBON MONOXIDE LIGHT 40. OUTSIDE AIR TEMP/VOLTMETER 19. CLUTCH ACTUATOR LIGHT 41. CYCLIC FRICTION 20. AUX FUEL PUMP LIGHT 42. CABIN HEAT 21. ALT LOW VOLTAGE LIGHT 43. ELT SWITCH (OPTIONAL) 22. ENGINE FIRE LIGHT 44. HSI SLAVE CONTROL OPTIONAL INSTRUMENT PANEL (EARLIER AIRCRAFT) (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 5 MAR 2015 7-21 21. ENGINE FIRE LIGHT 22. OIL PRESSURE LIGHT 23. GOVERNOR-OFF LIGHT 1. VERTICAL SPEED INDICATOR 24. FULL THROTTLE LIGHT 2. OPTIONAL INSTRUMENT 25. ROTOR BRAKE LIGHT 3. AIRSPEED INDICATOR 26. IGNITION SWITCH 4. ENGINE AND ROTOR TACHS 27. CLUTCH ACTUATOR SWITCH 5. OPTIONAL INSTRUMENT 28. PILOT’S SIDE CONSOLE (OPT’L) 6. OPTIONAL INSTRUMENT 29. OUTSIDE AIR TEMP/VOLTMETER 7. ALTIMETER 30. PANEL LIGHTS DIMMER 8. MANIFOLD PRESSURE GAGE 31. ENGINE INSTRUMENTS 9. CLOCK 32. CABIN AIR 10. CLUTCH ACTUATOR LIGHT 33. NAVIGATION LIGHTS SWITCH 11. M.R. GEARBOX TEMP LIGHT 34. ANTI-COLLISION LIGHT SWITCH 12. M.R. GEARBOX CHIP LIGHT 35. AVIONICS MASTER SWITCH 13. CARBON MONOXIDE LIGHT 36. ALTERNATOR SWITCH 14. STARTER-ON LIGHT 37. BATTERY SWITCH 15. T.R. GEARBOX CHIP LIGHT 38. MIXTURE CONTROL 16. LOW FUEL LIGHT 39. AVIONICS STACK 17. LOW RPM LIGHT 40. CYCLIC FRICTION 18. FUEL FILTER LIGHT 41. CABIN HEAT 19. AUX FUEL PUMP LIGHT 42. ELT SWITCH (OPTIONAL) 20. ALT LOW VOLTAGE LIGHT 43. PITOT HEAT SWITCH (OPT’L) INSTRUMENT PANEL – TYPICAL (LATER AIRCRAFT) (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) ROBINSON MODEL R44 II THIS PAGE INTENTIONALLY BLANK ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 7 MAY 2018 7-22 ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-23 AUDIO SYSTEM A four-place intercom/audio system is standard and is controlled by a small control panel above the avionics stack. The ICS volume knob controls intercom volume but does not affect radio volume. The VOX squelch knob is used to set the threshold volume at which the intercom is activated. When the VOX knob is turned fully clockwise, keying is required to activate the intercom. A toggle switch allows selection of PILOT ISO mode in which the pilot is connected only to the radio while the copilot and rear passengers remain connected to each other via the intercom. A music input jack is located on the aft seat console. This input is muted when the intercom is active, when transmitting, and during reception of radio signals. Headset jacks are located in the ceiling near each seat. The cyclic grips are equipped with trigger-style intercom/ transmit switches. The first trigger switch detent activates the intercom and the second detent transmits. Additional intercom buttons are located inboard of the rear seats and on the left forward floor or seat support. Audio control panels from several manufacturers are offered as options in place of the standard intercom system. Pilots should consult the manufacturer’s operating instructions if an audio panel is installed. OPTIONAL AVIONICS A wide range of optional avionics are available for the R44. It is not practical to provide a description of all equipment in this manual. All aircraft are delivered with the manufacturers’ operating manuals for each piece of installed equipment. Pilots are referred to the manufacturers’ manuals for detailed operating instructions. Good practice dictates becoming familiar with installed equipment before operating an aircraft. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-24 PITOT-STATIC SYSTEM The pitot-static system supplies air pressure to operate the airspeed indicator, altimeter, and vertical speed indicator. The pitot tube is located on the front edge of the mast fairing. The static sources are located on each side of the cabin aft of the rear doors. Water can be drained from pitot-static lines by removing the plastic drain plugs which are accessible through the forward inspection panel on the underside of the cabin. Draining lines should be required only if the airspeed indicator or altimeter appears erratic. Pitot and static sources should be inspected frequently to verify no bugs or other obstructions. DUAL TACHOMETER An electronic engine and rotor dual tachometer is standard. Engine tachometer signal is provided by magneto breaker points. Rotor tachometer signal is provided by two magnetic senders at the main gearbox drive yoke. Each tachometer is on a separate circuit with its own circuit breaker. With battery and alternator switches off, the tachometers continue to receive power from the battery through a bypass circuit as long as the clutch actuator switch is in the engage position. NOTE Do not stow helicopter with clutch switch engaged. The tachometers are powered with the clutch engaged and will discharge the battery. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-25 WARNING AND CAUTION LIGHTS Warning and caution lights include clutch, main gearbox over-temperature, main and tail gearbox chip, engine fire, starter on, low fuel, fuel filter, auxiliary fuel pump, low RPM, alternator, low oil pressure, rotor brake, carbon monoxide, governor off, and full throttle (later aircraft). The clutch light indicates that the clutch actuator is operating. The low RPM light and horn indicate rotor RPM at 97% or below. The engine fire light is actuated by a temperature switch located at the forward end of the horizontal firewall. The low oil pressure and low fuel lights are actuated by sensors in those systems and are independent of the gage indicators. The alternator light warns of a possible alternator failure. The auxiliary fuel pump light monitors fuel pressure from the auxiliary pump and illuminates due to pump failure or when the clutch switch is not engaged. The fuel filter light warns of possible filter contamination. The governor-off light indicates the RPM governor is switched off. The main and tail gearbox chip detectors are magnetic devices located in the drain plug of each gearbox. When metallic particles are drawn to the magnets they close an electrical circuit, illuminating the caution light. Metal particles may be caused by a failing bearing or gear, thus giving warning of impending gearbox failure. The main gearbox over-temp light is actuated by a temperature switch located near the input pinion. The carbon monoxide light is actuated by a sensor above the pilot’s heater outlet and indicates elevated cabin carbon monoxide levels. The full throttle light is activated by a switch in the throttle linkage and indicates that the engine is near full throttle. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-26 CABIN HEATING AND VENTILATION Fresh air vents are located in each door and in the nose. Door vents are opened and closed using the knob near the vent door hinge. A rotating knob is provided to lock vents closed. For maximum ventilation, open door vents wide during hover but only one inch or less during cruise. The rotating knob can be used to hold vents partially open. The fresh air inlet in the nose is opened by pulling the vent handle on console face. Rotating the vent handle clockwise will lock its position. Air from the nose inlet is directed along inside surface of the windshield for defogging as well as for ventilation. The cabin heater consists of a muffler heat shroud, a control valve at the firewall, outlets forward of the tail rotor pedals and in the rear footwells, and interconnecting ducting. A heater control knob located to the left of the cyclic center post actuates the valve which directs heat either into the cabin or out an overboard discharge on the cabin underside. CAUTION In case of an in-flight engine fire, cabin heat should be turned off to seal cabin area from engine compartment. SEATS, BELTS, AND BAGGAGE The seats are not adjustable but the pilot-side pedals are adjustable. Each helicopter is supplied with a cushion which can be placed behind the pilot to position him farther forward. This allows shorter pilots to reach the pedals, the cyclic grip in its most forward position, and controls on the center console. Each seat is equipped with a combined lap belt and inertia reel shoulder strap. The inertia reel is normally free but will lock if there is sudden movement as would occur in an accident. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 7 MAY 2018 7-27 SEATS, BELTS, AND BAGGAGE (cont’d) Four- or five-point harnesses are optional for the front seats. The lap belts on these harnesses should be adjusted to eliminate slack. On five-point harnesses, the lower strap should be adjusted as necessary to ensure that the buckle does not interfere with the cyclic in the full aft position. Later harnesses are equipped with a webbing stop located above the inertia reel. The stop limits shoulder strap retraction and should be adjusted so the straps are comfortable without excessive slack. A baggage compartment is located under each seat. Seat cushions hinge forward for access. Optional anchor loops located in the cabin ceiling above the door posts provide attachment points for a safety tether for equipment or occupants during doors-off operation. LANDING GEAR A skid-type landing gear is used. Most hard landings will be absorbed elastically. However, in an extremely hard landing, the struts will hinge up and outward as the crosstube yields (becomes permanently bent) to absorb the impact. Slight crosstube yielding is acceptable. However, yielding which allows the tail skid to be within 30 inches of the ground when the helicopter is sitting empty on level pavement requires crosstube replacement. The four landing gear struts are fitted with aerodynamic fairings to reduce air drag. The helicopter is approved to fly with or without the fairings installed. Abrasion-resistant wear shoes are mounted on the bottom of the skids. These shoes should be inspected periodically, particularly if autorotation landings with ground contact have been performed. Have skid shoes replaced whenever the thinnest point in the wear area is less than 0.06 inches (1.5 mm). ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-28 ROTOR BRAKE The rotor brake is mounted on the aft end of the main gearbox and is actuated by a cable connected to a pull handle located on the cabin ceiling. To stop the rotor, use the following procedure: 1. After pulling mixture off, wait at least 30 seconds. 2. Pull brake handle forward and down using moderate force (approximately 10 lb). 3. After rotor stops, it is recommended to use the rotor brake as a parking brake by hooking bead chain in slot in bracket. The brake must be released before starting the engine. When the brake is engaged, the starter buttons are disabled. CAUTION Applying rotor brake without waiting at least 30 seconds after engine stops or using a force which stops rotor in less than 20 seconds may damage brake shoes. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-29 CARBON MONOXIDE DETECTOR The carbon monoxide (CO) detector indicates elevated cabin CO levels. CO is an odorless, toxic gas present in engine exhaust which causes headaches, drowsiness, and possible loss of consciousness. CO levels may become elevated due to an exhaust leak or exhaust recirculation during prolonged hovering. The CO detector system consists of a sensor above the pilot’s heater outlet and a caution light. A system check (light flashes twice) is performed each time power is switched on. A sensor malfunction is indicated by a continuing flash every four seconds. If the caution light illuminates, shut off heater and open nose and door vents as required to ventilate the cabin. If hovering, land or transition to forward flight. If symptoms of CO poisoning (headache, drowsiness, dizziness) accompany caution light, land immediately. Have exhaust system inspected before next flight. Many chemicals can damage the CO sensor. Avoid use of solvents, detergents, or aerosol sprays near the sensor. Temporarily tape off openings in top and bottom of sensor housing when cleaning cabin interior. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 OCT 2016 7-30 EMERGENCY LOCATOR TRANSMITTER (OPTIONAL) The Emergency Locator Transmitter (ELT) installation consists of a transmitter with internal battery pack, an external antenna, and a remote switch/annunciator. The transmitter is mounted to the upper steel tube frame and is accessible through the aft, upper cowl door. The remote switch/annunciator is located left of the cyclic stick. The ELT is operated by a switch on the transmitter and a remote switch in the cockpit. The transmitter switch has been secured in the AUTO or ARM position at installation and should always be in this position for flight. The remote switch/annunciator is a three position switch with indicator light. This switch should also be in the AUTO or ARMED (middle) position for flight. With both switches set to AUTO/ARM, the ELT will begin transmitting when subjected to a high “G” load. When the unit is transmitting, the red indicator light illuminates. Moving the remote switch to ON activates the transmitter. Use the ON position if an emergency landing is imminent and time permits. If the ELT is inadvertently activated, use the RESET position of the remote switch to stop transmission and reset the unit. The red indicator will extinguish when unit is reset. For more detailed instructions on ELT operation, maintenance, and required tests, refer to manufacturer’s instructions supplied with the unit. ROBINSON MODEL R44 II SECTION 7 SYSTEMS DESCRIPTION ISSUED: 21 OCT 2016 7-31 OPTIONAL ACCESSORY MOUNTS Provisions for mounting small, portable items are an option. The provisions use mounting bars located forward of the pilot’s seat, the copilot’s seat, or both. The bars are fitted with one or more clamp assemblies which are compatible with a variety of commercially available accessory mounts. There is a 10 lb total weight limit for items attached to each bar. USB and cigarette-lighter-style power outlets are installed near the inboard end of the mounting bars. The power outlets are protected by the Aux Power circuit breaker and in-line fuses and are placarded with voltage/ current ratings. Wire clamps and a pocket for securing excess wire are also provided. The accessory mounts are intended to provide a safe means of mounting small items such as portable electronic devices. The mounting bar, clamp assembly, and power outlets are approved as part of the aircraft type design, but any items attached are the responsibility of the pilot in command under appropriate operating rules. Ensure that any items attached are secure and do not interfere with flight controls or primary field of view. Route any wires through the wire clamps or secure them to the bar with cable ties or tape. INTENTIONALLY BLANK SECTION 8 HANDLING AND MAINTENANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1 Required Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1 Required Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2 Preventive Maintenance by the Pilot . . . . . . . . . . . . . . . 8-3 Alterations to Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . 8-4 Ground Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-5 Parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-6 Cabin Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-6 Engine Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7 Tail Rotor Gearbox Oil . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9 Hydraulic Fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9 Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-10 Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-11 Cleaning Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-12 REVISED: 5 MAR 2015 8-i ROBINSON MODEL R44 II SECTION 8 HANDLING AND MAINTENANCE REVISED: 5 MAR 2015 8-1 SECTION 8 HANDLING AND MAINTENANCE GENERAL This section outlines procedures recommended for handling, servicing, and maintaining the R44 II helicopter. Every owner should stay in close contact with a Robinson Service Center to obtain the latest service and maintenance information. Owners should also be registered with the factory to receive service bulletins, changes to this handbook, and other helpful information as it becomes available. Federal Regulations place responsibility for maintenance of a helicopter on the owner and operator. The owner/ operator must insure that all maintenance is performed by qualified mechanics and in accordance with the R44 Maintenance Manual (Instructions for Continued Airworthiness), Service Bulletins/Service Letters, and FAA Airworthiness Directives. All limits, procedures, safety practices, time limits, servicing, and maintenance requirements contained in this handbook are considered mandatory. Authorize