ROBINSON MODEL R66

Engine anti-ice must be on for operation in visible moisture in ambient temperatures at or below 4°C (40°F). FUEL LIMITATIONS APPROVED FUEL GRADES Grade (Specification) Operating Limits Jet A or Jet A1 (ASTM D 1655) Anti-icing additive may be required (see below). Not approved for ambient tem- peratures below –32ºC (–25ºF). Jet B (ASTM D 6615) Anti-icing additive may be required (see below). Not approved for ambient tem- peratures above 32ºC (90ºF) at altitudes above 5000 feet. JP-4 (MIL-DTL-5624) Not approved for ambient temperatures above 32ºC (90ºF) at altitudes above 5000 feet. JP-5 (MIL-DTL-5624 Not approved for ambient temperatures below –32ºC (–25ºF). JP-8 (MIL-DTL-83133) Not approved for ambient temperatures below –32ºC (–25ºF). No. 3 Jet Fuel (P.R. China GB G537-2006) Anti-icing additive may be required (see below). Not approved for ambient tem- peratures below –32ºC (–25ºF). Anti-icing additive conforming to MIL-DTL-85470 must be added to Jet A, Jet A1, Jet B, or No. 3 Jet Fuel when ambient temperature is below 4ºC (40ºF). Check with fuel supplier to determine if supply includes additive. If not, add per manufacturer’s instructions. FUEL CAPACITY Total capacity: 74.6 US gallons (282 liters) Usable capacity: 73.6 US gallons (279 liters) ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 15 APR 2014 2-7 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 15 APR 2014 2-8 INSTRUMENT MARKINGS NOTE Red lines offset so instrument pointer does not enter red. See color code on page 2-1. AIRSPEED INDICATOR Green arc 0 to 140 KIAS Red cross-hatch 100 KIAS Red line 140 KIAS ROTOR TACHOMETER Lower red line 88% Green arc 88 to 106% Upper red line 106% ENGINE TACHOMETER (N 2 ) Yellow arc 78 to 88% Power on – transient operation only. (No restrictions during autorotation.) Lower red line 99% Green arc 99 to 101% Upper red line 101% GAS PRODUCER TACHOMETER (N 1 ) Green arc 60 to 105% Red line 105% MEASURED GAS TEMPERATURE Green arc 150 to 706ºC Yellow arc (5 minute limit) 706 to 782ºC Red line 782ºC Red dot (start limit) 927ºC ENGINE OIL TEMPERATURE Green arc 0 to 107ºC Red line 107ºC ENGINE OIL PRESSURE Lower red line 50 psi Yellow arc (below 78% N 1 ) 50 to 90 psi Green arc 90 to 130 psi Yellow arc (start and warm up) 130 to 150 psi Upper red line 150 psi 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 and 500 feet AGL . . . . . . . . . . 3-2 Power Failure Below 8 feet AGL . . . . . . . . . . . . . . . . . . 3-2 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 During Forward Flight . . . . . . . 3-5 Loss of Tail Rotor Thrust During Hover . . . . . . . . . . . . . 3-5 Engine Fire During Start or Shutdown . . . . . . . . . . . . . . 3-6 Engine Fire During Flight . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Electrical Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Tachometer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Hydraulic System Failure . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Power Turbine Governor Failure . . . . . . . . . . . . . . . . . . . 3-7 Red Warning Indicators . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Amber Caution Indicators . . . . . . . . . . . . . . . . . . . . . . . 3-8 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 16 APR 2013 3-i SECTION 3 EMERGENCY PROCEDURES DEFINITIONS Land Immediately - Land on the nearest clear area where a safe 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 engine oil pressure light, or decreasing N 1 or N2 RPM. A drive system failure may be indicated by an unusual noise or vibration, nose right or left yaw, or decreasing rotor RPM while N 2 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 speed. CAUTION Do not apply aft cyclic during touchdown or ground slide to prevent possible blade strike to tailcone. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-1 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-2 POWER FAILURE ABOVE 500 FEET AGL 1. Lower collective immediately to maintain rotor RPM. 2. Establish a steady glide at approximately 70 KIAS. (For maximum glide distance or minimum rate of descent, see page 3-3.) 3. Adjust collective to keep RPM between 95 and 106% or apply full down collective if light weight prevents attaining above 95%. 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 95 and 106% or apply full down collective if light weight prevents attaining above 95%. 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. POWER FAILURE BELOW 8 FEET AGL 1. Apply right pedal as required to prevent yawing. 2. Allow helicopter to settle. 3. Raise collective just before touchdown to cushion landing. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES MAXIMUM GLIDE DISTANCE CONFIGURATION 1. Airspeed approximately 90 KIAS. 2. Rotor RPM approximately 90%. Best glide ratio is about 5.5:1 or one nautical mile per 1100 feet AGL. MINIMUM RATE OF DESCENT CONFIGURATION 1. Airspeed approximately 60 KIAS. 2. Rotor RPM approximately 90%. Minimum rate of descent is about 1300 feet per minute. Glide ratio is about 4.5:1 or one nautical mile per 1350 feet AGL. CAUTION Increase rotor RPM to 95% minimum or full down collective when autorotating below 500 feet AGL. AIR RESTART PROCEDURE CAUTION Do not attempt restart if engine malfunction is suspected or before safe autorotation is established. An immediate restart may be attempted by pressing the start button if N1 is above 20% (within approximately 10 seconds of power loss). It is not necessary to close throttle or pull fuel cutoff for immediate restart. If N1 has decayed to 20% or below, use the following procedure: 1. Fuel cutoff - Pull OFF. 2. Throttle - Closed. 3. Start button - Push and release. 4. N1 15% or above - push fuel cutoff ON. 5. After peak MGT- throttle full open. FAA APPROVED: 16 APR 2013 3-3 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 close throttle and enter autorotation. 2. Maintain at least 70 KIAS if practical. 3. Select landing site 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 right yaw which cannot be stopped by applying left pedal. 1. Immediately close throttle to reduce yaw rate and allow aircraft to settle. 2. Raise collective just before touchdown to cushion landing. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-5 ENGINE FIRE DURING START OR SHUTDOWN Fire may be indicated by excessive MGT or by engine fire warning light. 1. Fuel cutoff – Pull OFF. 2. Start button – Push and release. 3. Fuel valve knob – Pull OFF. 4. Battery switch – OFF when MGT decreases to 150ºC or if fire worsens. 5. If time permits, apply rotor brake to stop rotors. 6. Exit aircraft. ENGINE FIRE IN FLIGHT 1. Immediately enter autorotation. 2. Cabin heat – OFF (if time permits). 3. If engine is running, land immediately, then pull fuel cutoff OFF and pull fuel valve knob OFF. If engine stops running, pull fuel cutoff OFF, pull fuel valve knob OFF, and complete autorotation landing. 4. If time permits, apply rotor brake to stop rotors. 5. Exit aircraft. ELECTRICAL FIRE 1. Battery and generator switches – OFF. 2. Open cabin vents. 3. Land Immediately. 4. Pull fuel cutoff OFF and pull fuel valve knob OFF. 5. If time permits, apply rotor brake to stop rotors. 6. Exit aircraft. NOTE Low RPM warning system is inoperative with battery and generator switches both OFF. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-6 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 16 APR 2013 3-7 TACHOMETER FAILURE If rotor or N2 tachometer malfunctions in flight, use remaining tach to monitor RPM. If it is not clear which tach is malfunctioning or if both tachs malfunction allow power turbine governor to control RPM and land as soon as practical. NOTE The rotor tach, N2 tach, and low RPM warning horn are each on separate circuits. A special circuit allows the battery to supply power to the tachs with the battery and generator 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. A run-on landing is recommended if a suitable landing surface is available. POWER TURBINE GOVERNOR FAILURE Governor failure is indicated by a rise or fall of N2 RPM. If N2 overspeeds, attempt to control RPM with throttle. If N2 underspeeds, verify throttle is full open and reduce collective to control RPM. If governor failure is suspected, land as soon as practical. If manual RPM control is not possible, lower collective, close throttle, and complete autorotation landing per power failure procedures. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-8 RED WARNING INDICATORS MR TEMP/ PRESS Indicates excessive temperature or low oil pressure in main gearbox. Land immediately. ENGINE FIRE Indicates possible fire in engine compart- ment. See procedures on page 3-6. ENGINE OIL Indicates loss of engine oil pressure. If oil pressure gage confirms pressure loss, land immediately. Otherwise, land as soon as practical. N1 below 50% RPM indicates a possible flameout and an air restart may be attempted. AMBER CAUTION INDICATORS MR CHIP Indicates metallic particles in main gearbox. See note below. TR CHIP Indicates metallic particles in tail gearbox. See note below. ENGINE CHIP Indicates metallic particles in engine. See note below. NOTE If chip light is accompanied by any indication of a problem such as noise, vibration, or temperature rise, land immediately. If there is no other indication of a problem, land as soon as practical. Break-in fuzz will occasionally activate chip lights. If no metal chips or slivers are found on detector plug, clean and reinstall (tail gearbox must be refilled with new oil). Hover for at least 30 minutes. If chip light comes on again, have affected gearbox serviced before further flight. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-9 AMBER CAUTION INDICATORS (cont’d) GEN Indicates generator failure. Turn off nonessential electrical equipment and switch GEN to RESET and back to ON. If light stays on, land as soon as practical. LOW FUEL Indicates approximately five gallons of usable fuel remaining. The engine will run out of fuel after 10 minutes at cruise power. CAUTION Do not use low fuel warning as a working indication of fuel quantity. FUEL FILTER Indicates fuel filter contamination. If no other indication of a problem exists, land as soon as practical. If light is accompanied by erratic engine operation, land immediately. LOW RPM A horn and caution light indicate that rotor speed is below 95% RPM. To restore RPM, immediately lower collective, verify throttle full open and, in forward flight, apply aft cyclic. Horn is disabled when collective is full down. COWL DOOR Indicates fuel filler cowl door, right engine cowl door, or baggage compartment door is not closed. Land as soon as practical. AIR FILTER Indicates air filter contamination or blockage. Engine is operating on unfiltered air via filter bypass doors. Land as soon as practical and inspect filter. EMU While annunciator panel test button is depressed, indicates Engine Monitoring Unit status. See description in Section 7. ROTOR BRAKE Indicates rotor brake is engaged. Release immediately in flight or before starting engine. SECTION 4 NORMAL PROCEDURES CONTENTS Page Recommended Airspeeds . . . . . . . . . . . . . . . . . . . . . . . 4-1 Daily or Preflight Checks . . . . . . . . . . . . . . . . . . . . . . . . 4-1 Cold Weather Operation . . . . . . . . . . . . . . . . . . . . . . . . 4-5 Before Starting Engine . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 Ground Power Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 Starting Engine and Run-Up . . . . . . . . . . . . . . . . . . . . . . 4-7 Takeoff Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10 Doors-Off Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10 Practice Autorotation - Power Recovery . . . . . . . . . . . . 4-11 Practice Autorotation - With Ground Contact . . . . . . . . . 4-12 Hydraulics-Off Training . . . . . . . . . . . . . . . . . . . . . . . . . 4-12 Approach and Landing . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13 Shutdown Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14 N 1 Deceleration Check . . . . . . . . . . . . . . . . . . . . . . . . . . 4-15 Noise Abatement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-16 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-i ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 FEB 2014 4-1 SECTION 4 NORMAL PROCEDURES RECOMMENDED AIRSPEEDS Takeoff and Climb 60 KIAS Maximum Range 100 KIAS* Landing Approach 60 KIAS Autorotation 70 KIAS * Certain conditions may require lower airspeed. See Vne placard in Section 2. DAILY OR PREFLIGHT CHECKS Remove all covers and tie-downs. 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, the main rotor hub may be reached by using the steps built into three cowl doors on the left side of the cabin. Check general condition of aircraft and verify no visible damage, fluid leakage, or abnormal wear. Verify no fretting at 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 tail gearbox Telatemp shows 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. DAILY OR PREFLIGHT CHECKS (cont’d) 1. Pilot’s Station Battery switch ON Check fuel quantity MR temp/press, engine oil, gen, low RPM lights on Test annunciator panel, all lights on Check strobe, nav, landing lights Battery switch OFF Release rotor brake Adjust tail rotor pedals, pins secure 2. Fuselage Right Side and Engine Compartment Verify no visible damage Verify door hinge cotter rings installed Check landing gear strut fairings, skid, skid shoes Verify static port clear Check baggage compartment loading and security Verify baggage door latched Verify engine air filter clean Verify no fluid leaks Verify all air ducts secure Check engine oil filter impending bypass indicator Check engine fuel control linkage Verify exhaust secure and no cracks Verify cowl door latched 3. Tailcone, Empennage, and Tail Rotor Verify all antennas and lights secure Verify empennage secure, no cracks Verify tail rotor guard secure, no cracks Verify tail skid secure, no damage Check tail rotor gearbox oil quantity and Telatemp Verify drive system continuity by rotating tail rotor Verify no damage to tail rotor blades Verify no looseness at pitch links, bellcrank Check condition of elastomeric teeter bearing Verify teeter bearing bolt does not rotate ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-2 DAILY OR PREFLIGHT CHECKS (cont’d) 4. Belly Verify all antennas and panels secure Verify aft crosstube cover properly installed Verify generator cooling air filter clean 5. Main Rotor Verify no damage to blades Verify paint covers bond line Verify no leaks at pitch change boots Verify all fasteners secure Verify no excessive looseness at scissors, rod ends CAUTION Do not pull down on blades to teeter rotor. To lower a blade, push up on opposite blade. 6. Fuselage Left Side and Engine Compartment Verify no visible damage Verify door hinge cotter rings installed Check landing gear strut fairings, skid, skid shoes Verify static port clear Verify fuel quantity and filler cap secure Verify engine air filter clean and secure Check engine, main gearbox, hydraulic oil levels Check gearbox oil filter impending bypass indicator Check engine and gearbox oil coolers Check engine governor control linkage Verify no fluid leaks Sample fuel, drain water and contaminants Verify all cowl doors latched 7. Nose Verify pitot tube clear Verify windshield clean and undamaged ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-3 DAILY OR PREFLIGHT CHECKS (cont’d) 8. Cabin Area Verify no loose items Verify all items clear of controls Verify left seat controls removed or properly installed Verify seatbelts for unoccupied seats buckled CAUTION Remove left seat controls if person in that seat is not a rated helicopter pilot. CAUTION Ensure compartments under occupied seats are not filled above maximum fill line. CAUTION Ensure all cabin doors are unlocked before flight to allow rescue or exit in an emergency. Aft door locks have a green stripe to indicate door unlocked. CAUTION Shorter pilots may require cushion to obtain full travel of all controls. Verify aft cyclic travel is not restricted. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-4 COLD WEATHER OPERATION Special precautions should be taken if the helicopter is to be started after a cold soak below 4°C (40°F). Since a cold battery has significantly reduced capacity, pre-heating the battery is recommended. Use auxiliary ground power if available. For consistent starts, use fuels optimized for cold weather (Jet B, JP-4). A fuel anti-icing additive may be required (see Section 2). After start, ensure engine oil temperature is 0°C minimum before increasing RPM above idle. If cold soaked below -18°C (0°F), pre-heat the battery and engine fuel control area. The engine fuel control area may be pre-heated using a space heater. When cold soaked to -35°C (-31°F) and heated with a 3000 BTU/hr (900 W) space heater, it will require approximately 20 minutes to pre-heat the fuel control unit. CAUTION Do not use an open flame heater to pre-heat the engine or battery. CAUTION Ice in engine fuel control air circuits following a cold soak may cause uncontrolled engine acceleration during starting. If uncontrolled acceleration occurs, pull fuel cutoff OFF to shut down engine, then restart engine. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-5 BEFORE STARTING ENGINE Seat belts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fastened Fuel valve . . . . . . . . . . . . . . . . . . . . . . . ON, guard installed Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Cyclic, collective, pedals . . . . . . . . . . . . . . . Full travel free Collective . . . . . . . . . . . . . . . . . . . . . Full down, friction ON Cyclic . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral, friction ON Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral Rotor brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengaged Circuit breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . In Cabin heat, anti-ice, pitot heat . . . . . . . . . . . . . . . . . . . OFF Landing lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Avionics, generator switches . . . . . . . . . . . . . . . . . . . . OFF Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Set Hydraulic switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GROUND POWER START Have ground personnel connect ground power to external receptacle prior to engaging starter and disconnect once idle is stabilized prior to switching generator ON. Ground power is connected to the helicopter’s electrical system when battery switch is ON. Starts using ground power assist follow the same procedure as normal starts. NOTE If generator is switched ON prior to disconnecting ground power, high generator loads and reduction in idle speed may occur. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-6 STARTING ENGINE AND RUN-UP Battery, strobe switches . . . . . . . . . . . . . . . . . . . . . . . . ON Igniter (key) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Enable Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Fuel cutoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pull OFF Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Closed Start button . . . . . . . . . . . . . . . . . . . . . . . Push and release N1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15%, increasing MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Below 150°C Fuel cutoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Push on Light-off . . . . . . . . . . . . . . . . . . . . . . Within three seconds MGT . . . . . . . . . . . . . . . . . . . . . . . . Monitor, observe limits CAUTION Excessive MGT will cause severe engine damage. Do not push fuel cutoff ON unless N1 has reached adequate speed and is increasing. N1 above 15% is recommended; 12% N1 minimum may be used in cold weather. If MGT reaches limit during start or light-off does not occur within three seconds, immediately pull fuel cutoff OFF, wait ten seconds, then turn igniter switch OFF to stop starter. 25% N 1 . . . . . . . . . . . . . . . . . . . . . . . . . Main rotor rotating Oil pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . Increasing N 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stable at 65 to 67% Fuel cutoff guard . . . . . . . . . . . . . . Install, begin timing idle Ground power (if used) . . . . . . . . . . . . . . . . . . . . Disconnect Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Avionics switch, headsets . . . . . . . . . . . . . . . . . . . . . . . ON Annunciator panel test . . . . . . . . . . . . . . . . . . . All lights on Engine anti-ice check . . . . . . . . . . . . . . . . Annunciator light Doors . . . . . . . . . . . . . . . . . . . . . . . . . . Closed and latched Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Hydraulic system . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Lift collective slightly . . . . . . . . . . . . . . . . . . Low RPM horn Warm-up . . . . . . . . . . . . . . . Verify at least one minute idle Throttle . . . . . . . . . . . . . . . . . . Increase slowly to full open N 2 /R . . . . . . . . . . . . . . . . Stable at 100% (beep as required) Annunciator lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Engine gages . . . . . . . . . . . . . . . . . Normal operating range ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-7 STARTING ENGINE AND RUN-UP (cont’d) NOTE Time between starter engagement and idle should normally not exceed 40 seconds. If time exceeds 40 seconds but engine continues to accelerate, start attempt may be extended to one minute. If N1 is below 58% after one minute (or after 40 seconds if engine is not accelerating), pull fuel cutoff OFF, wait for MGT drop, and turn igniter (key) switch OFF to stop starter. To avoid overheating, allow one minute delay between start attempts. After three attempts, allow 30 minutes before next attempt. 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 One minute warm-up at idle not required within 15 minutes of last shutdown. NOTE When opening throttle, a target torque of at least 25% is recommended to minimize time transitioning through N 2 yellow arc. CAUTION When opening throttle, avoid exceeding 50% torque. On slippery surfaces, be prepared to counter nose-right rotation with left pedal. NOTE Before takeoff, pilot should uncover one ear and listen for any unusual noise which may indicate impending failure of a bearing or other component. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 15 APR 2014 4-8 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES TAKEOFF PROCEDURE 1. Verify doors latched, hydraulics ON, and RPM stabilized at 100%. 2. Engine anti-ice as required per Section 2. 3. Clear area. Slowly raise collective until aircraft is light on skids. Reposition cyclic as required for equilibrium, then gently lift aircraft into hover. Note hover torque. 4. Beep RPM as required to 100%. 5. Check gages in green, lower nose, and accelerate to climb speed following profile shown by height-velocity diagram in Section 5. Takeoff torque should not exceed 10% above hover torque. NOTE Takeoff portion of height-velocity diagram was demonstrated at 10% above hover torque to prevent excessive nose-down attitude. NOTE Periodically performing power assurance check (see Section 5) may provide indication of engine deterioration or air filter blockage. FAA APPROVED: 26 NOV 2013 4-9 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES CRUISE 1. Beep RPM as required to 100%. 2. Set torque as desired with collective. Observe torque, MGT, and Vne limits. 3. Verify gages in green, no cautions or warnings. 4. Engine anti-ice as required. CAUTION If turbulence is expected, reduce power and use a slower than normal cruise speed. NOTE Avoid large, rapid power changes. The engine governor reacts slowly and RPM excursions may occur. NOTE When loaded near aft CG limit, slight yaw oscillation 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 outboard seat bottoms may lift if not restrained. CAUTION Flight with left door(s) removed is not recommended. Loose objects exiting left doors may damage tail rotor. FAA APPROVED: 20 JAN 2015 4-10 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-11 PRACTICE AUTOROTATION - POWER RECOVERY CAUTION Verify a recent N 1 deceleration check was performed prior to conducting autorotations. Do not close throttle above 10,000 feet density altitude or with cabin heat ON (see Section 2). 1. Close throttle and lower collective to down stop. 2. Adjust collective to keep rotor RPM in green arc. 3. Keep airspeed 60 to 70 KIAS. 4. At about 40 feet AGL, begin cyclic flare to reduce rate of descent and forward speed, and smoothly roll throttle full on to recover engine power. 5. At about 8 feet AGL, apply forward cyclic to level aircraft, and raise collective to control descent. CAUTION Simulated engine failures require prompt lowering of collective to avoid dangerously low rotor RPM. Catastrophic rotor stall could occur if rotor RPM drops below 80% plus 1% per 1000 feet of altitude. CAUTION If entering autorotation with a rapid col- lective input, close throttle before lower- ing collective to avoid an RPM overspeed. CAUTION Engine may require several seconds to spool up to full power during power recoveries. NOTE For maximum glide distance and minimum rate of descent configurations, see Section 3. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 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 keep throttle closed throughout maneuver. 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 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 R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-13 APPROACH AND LANDING 1. Make final approach into wind at lowest practical rate of descent with initial airspeed of 60 knots. 2. Reduce airspeed and altitude smoothly to hover. (Be sure rate of descent is less than 300 feet per minute before airspeed is reduced below 30 KIAS.) 3. From hover, lower collective gradually until ground contact. 4. After initial ground contact, lower collective to full down position. CAUTION When landing on a slope, return cyclic control to neutral before closing throttle. CAUTION Never leave helicopter flight controls unattended while engine is running. CAUTION Hold throttle closed if passenger is entering or exiting left front seat with engine running and left seat collective installed. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-14 SHUTDOWN PROCEDURE Collective down . . . . . . . . . . . . . . . . . . . . . . . . Friction ON Throttle closed . . . . . . . . . . . . . . . . . N 1 deceleration check Cyclic and pedals neutral . . . . . . . . . . . . . . . . . Friction ON Cool down . . . . . . . . . . . . . . . . . . . . . . . . . Two minute idle Fuel cutoff . . . . . . . . . . . . . . . . . . . Pull OFF, monitor MGT CAUTION Rapid MGT increase following shutdown indicates residual fire in combustor. Follow “Engine Fire During Start or Shutdown” procedure per Section 3. Sprag clutch check . . . . . . . . . . . . Verify N 2 /R needles split Wait one minute . . . . . . . . . . . . . . . . . . . Apply rotor brake Avionics, generator, battery, igniter 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 start- up and shutdown to reduce possibility of unintentional hydraulics-off liftoff. Switch OFF only for pre-takeoff controls check or hydraulics-off training. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-15 N 1 DECELERATION CHECK The deceleration check is performed on the ground to confirm proper fuel control operation. The check should be performed after the last flight of the day. The check should also be performed during the preflight run-up if autorotations are planned during the flight. Improper deceleration may cause engine flameout during an autorotation entry. Perform check as follows: 1. Collective full down. 2. Throttle open, N 2 /R at 100%. 3. If N1 is below 80%, lift collective slightly to set N1 at 80%. 4. Rapidly close throttle and measure time for N 1 to reach 70% RPM. Minimum allowable time is two seconds. If deceleration time is less than two seconds, switch generator OFF and perform two more checks to confirm time. If confirmed time is less than two seconds, have helicopter serviced. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 NOV 2013 4-16 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 descent 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 judgement, they would result in an unsafe flight path. (OVER) RHC recommends inserting this sheet at the end of Section 4 of the R66 Pilot’s Operating Handbook. December 2014 AVOIDING HOT STARTS Exceeding temperature limits during a turbine start (a “hot start”) can cause severe engine damage requiring expensive repairs. Always follow the Starting Engine checklist and pay close attention to engine instruments during a start. Do not attempt a start when rushed or distracted. During a start, airflow through the engine controls the temperature of the combusting fuel. Spinning the compressor with the starter provides the required airflow. During an aborted start, fuel flow is stopped by pulling the fuel cutoff but the starter must continue providing airflow through the engine to control temperature. The R66 start circuit automatically keeps the starter engaged without the need to keep the starter button depressed. Normal engine starts should have peak measured gas temperature (MGT) below 800°C for cold engines or below 850°C for warm engines. If start temperatures are above these or are trending higher, engine maintenance may be required. Reduced power assurance margins accompanied by high start temperatures may indicate a dirty compressor. Fuel control adjustments can also affect start temperature. Consult a qualified turbine mechanic to diagnose any abnormal start characteristics. Before initiating a start: • Verify fuel cutoff is pulled completely off. • Verify twist grip is completely closed (rotated toward pilot). • Verify battery voltage is normal. If battery voltage is low (less than approximately 24.5 volts), use ground power and/or replace battery. Otherwise, the starter may not spin the compressor fast enough to provide the required airflow. During a start: • DO NOT push the fuel cutoff on until N1 is smoothly rising through at least 15% (see flight manual for cold weather starts). If the starter is sluggish or will not achieve 15%, do not introduce fuel. Switch starter off using igniter (key) switch. • If the engine is warm from a previous flight, DO NOT push fuel cutoff on until MGT is below 150°C. As the starter accelerates the engine to 15% N1 the MGT typically falls below 150°C. However, extra time may be required to allow the residual temperature to decrease. • After pushing the fuel cutoff on, CONTINUOUSLY MONITOR MGT and KEEP HAND ON FUEL CUTOFF until N1 is above 60%. • PULL FUEL CUTOFF IMMEDIATELY if MGT approaches 900°C. This is the most important action for stopping a hot start and should be an instinctive reaction. Wait at least 10 seconds or until MGT has decreased below 150°C. Then, switch starter off using igniter (key) switch. • Never push fuel cutoff back on if it has been pulled off. Finish aborting the start. Then, determine and correct the cause of the high temperature before attempting another start. ROBINSON MODEL R66 SECTION 5 PERFORMANCE FAA APPROVED: 26 NOV 2013 5-11 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 2015 7-i SECTION 7 SYSTEMS DESCRIPTION CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1 Rotor Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Drive System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Powerplant Installation . . . . . . . . . . . . . . . . . . . . . . . . . 7-4 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-5 Removable Flight Controls . . . . . . . . . . . . . . . . . . . . . . . 7-6 Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-7 Control Friction Adjustment . . . . . . . . . . . . . . . . . . . . . . 7-8 Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-8 Engine Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-9 Starter and Ignition System . . . . . . . . . . . . . . . . . . . . . . 7-10 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-11 Pitot-Static System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-11 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-12 Lighting System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-15 External Power Receptacle . . . . . . . . . . . . . . . . . . . . . . 7-16 Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-16 Annunciator Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-20 Dual Tachometer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-21 Audio System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22 Optional Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22 Engine Monitoring Unit . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Cabin Heating and Ventilation . . . . . . . . . . . . . . . . . . . . 7-24 Seats, Belts, and Baggage . . . . . . . . . . . . . . . . . . . . . . . 7-25 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-26 Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-27 Emergency Locator Transmitter (Optional) . . . . . . . . . . . 7-28 Optional Accessory Mounts . . . . . . . . . . . . . . . . . . . . . . 7-29 INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 2015 7-1 SECTION 7 SYSTEMS DESCRIPTION GENERAL The R66 is a five-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 and in various ducts and fairings. The cabin doors are also constructed of fiberglass and thermoplastics. Several cowl doors provide access to the drive system, engine, engine oil tank, fuel filler cap, and fuel sump drain. A right-side door provides access to the main baggage compartment. Additional access to controls and other components for maintenance is provided by removable panels and cowlings. The engine is located aft of the main baggage compartment. The engine compartment is isolated from the rest of the airframe by firewalls in front of and above the engine. The four cabin doors are removable. Refer to Section 8 for removal and installation procedures. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 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. Aluminum 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. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-5 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. The collective stick has a twist grip to provide input to the engine fuel control. Raising or lowering collective provides power turbine governor inputs via an interconnecting linkage. 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 R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 FEB 2014 7-6 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. 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 R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 2015 7-8 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 stick. Turning the knob clockwise applies friction to both longitudinal and lateral cyclic. CAUTION Control friction must be used with caution in 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. ENGINE CONTROLS A twist grip throttle control is located on each collective stick. The controls are interconnected and actuate the engine fuel control input lever via a push-pull cable. The throttle is normally not used for control but is set either fully closed (idle position) or fully open. The engine incorporates a hydromechanical governor which attempts to maintain 100% engine output shaft RPM when the throttle is in the open position. A linkage provides the power turbine governor with collective inputs to help anticipate changing power demands. Large power changes or varying environmental conditions may cause the governor RPM setting to vary by a few percent. A momentary toggle switch (beep switch) on the collective stick is provided to trim, or “beep”, the governor setting to the desired RPM. The switch controls an actuator which adjusts the linkage between the collective and power turbine governor. Holding the beep switch up or down will change rotor RPM approximately one percent per two seconds. REVISED: 20 JAN 2015 7-13 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM ELECTRICAL SYSTEM (cont’d) REVISED: 20 JAN 2015 7-14 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION ELECTRICAL SYSTEM (cont’d) CIRCUIT BREAKER PANEL – TYPICAL ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 26 NOV 2013 7-15 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. A light at the top of the windshield and post lights illuminate the instrument panel. Panel 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 with high and low settings. The map light may be used for emergency lighting of the instrument panel. An additional cabin light with an adjacent switch is located just aft of the map light. The map and cabin lights are not connected to the dimmer circuit. Two long-life, high intensity discharge (HID) landing lights are installed in the nose. One wide-angle and one narrow- beam light are used to increase lighted area. One landing light switch controls both lights and is located on the cyclic center post. 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 an additional position on the strobe switch. On later aircraft, the optional light is controlled by a separate switch. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 26 NOV 2013 7-16 EXTERNAL POWER RECEPTACLE A 28-volt MS3506-compatible receptacle is provided for external power. On earlier aircraft, the receptacle is located inside the right engine cowl door. On later aircraft, the receptacle is located in the cabin outboard of the pilot’s seat. 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. Provisions are provided to allow battery charging when the battery switch is off. See Section 8 for charging procedures. INSTRUMENT PANEL Standard primary instruments include an airspeed indicator, engine (N 2 ) and rotor dual tachometer, altimeter, torque meter, and magnetic compass. Engine gages include an N 1 tachometer, measured gas (turbine) temperature, oil pressure, oil temperature, and fuel quantity. Also standard are a clock, an ammeter, a digital outside air temperature gage/voltmeter, and an hourmeter. An additional hourmeter is located outboard of the pilot’s seat. Both hourmeters require main gearbox oil pressure to activate. The outboard hourmeter is collective activated and may be used to determine 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. INSTRUMENT PANEL – TYPICAL (EARLIER AIRCRAFT) (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) 1. VERTICAL SPEED INDICATOR 18. PANEL LIGHTS DIMMER 2. OPTIONAL INSTRUMENT 19. NAVIGATION LIGHTS SWITCH 3. AIRSPEED INDICATOR 20. STROBE LIGHT SWITCH 4. N 2 AND ROTOR TACHOMETERS 21. AVIONICS MASTER SWITCH 5. ALTIMETER 22. GENERATOR SWITCH 6. OPTIONAL INSTRUMENT 23. BATTERY SWITCH 7. TORQUEMETER 24. IGNITER SWITCH 8. ANNUNCIATOR PANEL 25. CABIN AIR 9. ANNUNCIATOR TEST BUTTON 26. OUTSIDE AIR TEMP/VOLTMETER 10. CLOCK 27. HOURMETER 11. ENGINE OIL TEMP GAGE 28. FUEL CUTOFF WITH GUARD 12. ENGINE OIL PRESSURE GAGE 29. AUDIO CONTROL PANEL 13. AMMETER 30. CYCLIC FRICTION 14. FUEL GAGE 31. CABIN HEAT 15. MGT GAGE 32. ELT SWITCH (OPTIONAL) 16. N 1 TACHOMETER 33. ANTI-ICE SWITCH 17. ROTOR BRAKE LIGHT 34. HEATED PITOT SWITCH (OPT’L) ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 26 NOV 2013 7-17 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 1. VERTICAL SPEED INDICATOR 20. IGNITER SWITCH 2. OPTIONAL INSTRUMENT 21. MGT GAGE 3. AIRSPEED INDICATOR 22. N 1 TACHOMETER 4. N 2 AND ROTOR TACHOMETERS 23. CABIN AIR 5. OPTIONAL INSTRUMENT 24. NAVIGATION LIGHTS SWITCH 6. OPTIONAL INSTRUMENT 25. ANTI-COLLISION LIGHT SWITCH 7. ALTIMETER 26. AVIONICS MASTER SWITCH 8. TORQUEMETER 27. GENERATOR SWITCH 9. CLOCK 28. BATTERY SWITCH 10. ANNUNCIATOR PANEL 29. FUEL CUTOFF WITH GUARD 11. ANNUNCIATOR TEST BUTTON 30. AUDIO CONTROL 12. PILOT’S SIDE CONSOLE (OPT’L) 31. AVIONICS STACK 13. AMMETER 32. HOURMETER 14. ENGINE OIL TEMP GAGE 33. CYCLIC FRICTION 15. OUTSIDE AIR TEMP/VOLTMETER 34. CABIN HEAT 16. ENGINE OIL PRESSURE GAGE 35. ELT SWITCH (OPTIONAL) 17. PANEL LIGHTS DIMMER 36. PITOT HEAT SWITCH (OPT’L) 18. FUEL GAGE 37. ENGINE ANTI-ICE SWITCH 19. ROTOR BRAKE LIGHT REVISED: 26 NOV 2013 7-18 INSTRUMENT PANEL – TYPICAL (LATER AIRCRAFT) (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) REVISED: 20 JAN 2015 7-19 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 1. AIRSPEED INDICATOR 19. GPS NAVIGATOR 2. N2 AND ROTOR TACHOMETERS 20. IGNITER SWITCH 3. ALTIMETER 21. ROTOR BRAKE ANNUNCIATOR 4. TORQUEMETER 22. CABIN AIR 5. MULTI-FUNCTION DISPLAY 23. NAVIGATION LIGHTS SWITCH 6. ANNUNCIATOR PANEL 24. ANTI-COLLISION LIGHT SWITCH 7. ANNUNCIATOR TEST BUTTON 25. AVIONICS MASTER SWITCH 8. PRIMARY FLIGHT DISPLAY 26. GENERATOR SWITCH 9. OPTIONAL INSTRUMENT 27. BATTERY SWITCH 10. CLOCK 28. FUEL CUTOFF WITH GUARD 11. AMMETER 29. AUDIO CONTROL 12. OUTSIDE AIR TEMP/VOLTMETER 30. AVIONICS STACK 13. PANEL LIGHTS DIMMER 31. HOURMETER 14. ENGINE OIL TEMP GAGE 32. CYCLIC FRICTION 15. MGT GAGE 33. CABIN HEAT 16. ENGINE OIL PRESSURE GAGE 34. ELT SWITCH (OPTIONAL) 17. FUEL GAGE 35. PITOT HEAT SWITCH (OPT’L) 18. N1 TACHOMETER 36. ENGINE ANTI-ICE SWITCH OPTIONAL INSTRUMENT PANEL (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) REVISED: 20 JAN 2015 7-20 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION ANNUNCIATOR PANEL The annunciator panel consists of illuminated segments located at the top of the main instrument panel. If a caution or warning condition occurs, the appropriate segment(s) illuminate indicating the nature of the problem. The CHIP segments are illuminated by magnetic chip detectors in each gearbox which collect metallic particles in order to complete an electric circuit. The engine gearbox has two chip detectors, either of which can illuminate the ENGINE CHIP segment. The MR TEMP/PRESS segment is illuminated by either the temperature switch or oil pressure switch at the main gearbox. The ENGINE FIRE segment is illuminated by a temperature switch in the engine compartment. The ENGINE OIL segment is activated by a pressure switch which is independent of the oil pressure sender. The ANTI ICE segment illuminates via a pressure switch in the engine anti-ice air line. The GEN segment illuminates when the generator is disconnected from the main electrical bus. The LOW FUEL segment is illuminated by a float switch in the tank which is independent of the fuel quantity sender. The FUEL FILTER segment illuminates when a pressure switch detects excessive pressure drop across the fuel filter. The LOW RPM segment is illuminated by a sensor measuring driveline speed at the aft end of the main gearbox. A horn sounds simultaneously with illumination of the LOW RPM segment when rotor speed is below 95% RPM. The horn is disabled when the collective is fully down. The COWL DOOR segment is illuminated when the fuel filler cowl door, the baggage door, or, on earlier aircraft, the right engine cowl door (which accesses the external power receptacle) is not closed. The AIR FILTER segment illuminates when pressure drop across the filter opens bypass doors, allowing unfiltered air to the engine. REVISED: 20 JAN 2015 7-21 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION ANNUNCIATOR PANEL (cont’d) The EMU (Engine Monitoring Unit) segment indicates the EMU status with either steady, flashing, or no illumination. The EMU segment will illuminate only when the test button is depressed. A push-to-test button on the instrument panel should cause all segments on the annunciator panel, as well as the ROTOR BRAKE light, to illuminate when depressed. The LOW FUEL segment takes approximately two seconds before it illuminates due to a time delay in the circuit. (The time delay prevents sloshing fuel from giving a false indication.) If the LOW FUEL segment illuminates immediately after the test button is depressed, a fault is indicated and should be investigated by a qualified mechanic. The EMU segment takes approximately ten seconds to perform a self-test after the battery is switched ON before it will illuminate. The test button may be used on the ground or in flight to verify all circuits are functioning. DUAL TACHOMETER An electronic engine (N2) and rotor dual tachometer is standard. Engine tachometer signal is provided by a transducer on the engine gearbox. Rotor tachometer signal is provided by magnetic senders at the main gearbox tail rotor driveline yoke. Each tachometer is on a separate circuit with its own circuit breaker. The tachometer bus receives power from the avionics bus or through the battery relay bypass circuit as long as the main rotor gearbox has oil pressure. Therefore, the tachometers will receive power through the bypass circuit whenever the rotors are turning even if the avionics bus is not powered. The bypass circuit is disconnected from the tachometer bus when the annunciator test button is depressed. Pressing the test button while the helicopter is running will confirm that the tachometers are receiving power from the avionics bus. REVISED: 20 JAN 2015 7-22 AUDIO SYSTEM A five-place audio system is standard. An audio control panel allows control of communication radios, intercom, and music (or other external audio) input. Audio control panels from several manufacturers are offered. Pilots should consult the manufacturer’s operating instructions for the specific brand of audio panel in the aircraft they fly. Headset jacks are located in the ceiling near each seat. Pilot and copilot intercom and transmit are controlled by trigger switches on the cyclic grips. The trigger has two detents; the first detent activates the intercom and second detent transmits. Additional intercom buttons are located on the forward side of the rear seats and on the left forward floor. Intercom may also be set to be voice activated. Music or other external audio may be plugged into a jack on the circuit breaker panel. For most installations and settings, this input is muted during radio communication. OPTIONAL AVIONICS A wide range of optional avionics are available for the R66. 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 R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 2015 7-23 ENGINE MONITORING UNIT The Engine Monitoring Unit (EMU) is a digital recording device mounted behind the right rear seatback panel. The EMU continuously monitors N1, N2, engine torque, and MGT. EMU status is indicated by the EMU segment on the annunciator panel. The EMU segment will only illuminate while the annunciator panel test button is depressed. The EMU requires approximately ten seconds to complete a self-test after the aircraft battery is switched on. Once the self-test is complete, steady illumination of the annunciator means normal EMU operation. A slowly flashing indication (once every two seconds) or no illumination means there is a fault in the EMU’s senders or circuitry. A fast flashing indication (four times per second) is given if the EMU has detected an exceedance. A fault or exceedance indication should be investigated and reset by a qualified mechanic prior to the next flight. The EMU records exceedances of Rolls-Royce engine limits. The EMU also records a start cycle when N1 exceeds 30% and MGT is at least 343°C. EMU data can be downloaded to a computer with the appropriate software. The EMU is intended to be used only as a maintenance aid. It is the pilot’s responsibility to report any observed exceedances and the operator’s responsibility to maintain a record of engine starts and time in service. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 20 JAN 2015 7-24 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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 seal and 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 the console face. Rotating the vent handle clockwise will lock its position. Air from the nose inlet is directed along the inside surface of the windshield for defogging as well as for ventilation. Bleed air from the engine compressor is used for cabin heat. Tubing routes hot air from the engine to outlets forward of the tail rotor pedals and in the rear footwells. A heater control knob located to the left of the cyclic stick actuates a valve in the aft end of the control tunnel through a push- pull cable to control cabin heat. Because the cabin heat uses engine compressor air, some performance degradation occurs with heat ON (see Section 5). CAUTION In case of engine fire, cabin heat should be turned OFF. REVISED: 20 JAN 2015 7-25 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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 the 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. Five-point harnesses are optional for the front seats. The lap belts on these harnesses should be adjusted to eliminate slack. The lower strap should be adjusted as necessary to ensure that the buckle does not interfere with the cyclic grip at aft cyclic. The harness is 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. The main baggage compartment is located between the cabin and the engine compartment. It is accessed via a large door on the aircraft right side. The cowl door annunciator illuminates to warn the pilot when the door is not latched. A light illuminates the compartment when the battery switch is ON. Tie down anchors are provided for securing items in the baggage compartment. Observe placarded weight limits. Additional compartments are located under each seat except the center rear seat. Seat cushions hinge forward for access to these compartments. Do not load these compartments above the maximum fill lines. The lines indicate required crush space for the seats in an accident. REVISED: 20 JAN 2015 7-26 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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 38 inches of the ground (30 inches for extended gear) 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). REVISED: 20 JAN 2015 7-27 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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 fuel cutoff, wait at least one minute. 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. An annunciator light near the igniter switch illuminates when the brake is engaged. The brake must be released before starting the engine. When the brake is engaged, the starter is disabled. CAUTION Applying rotor brake without waiting at least one minute after engine shutdown or using a force which stops rotor in less than ten seconds may damage brake shoes. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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 spring loaded air intake door in the right-side cowl. The remote switch/annunciator is located left of the cyclic stick. The ELT is operated by a switch on the transmitter and by the remote switch. The transmitter switch has been set in the 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 be in the ARMED position for flight. With both switches set to armed, 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 momentary RESET & TEST 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 manual supplied with the unit. REVISED: 20 JAN 2015 7-28 ISSUED: 20 JAN 2015 7-29 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION 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. THIS PAGE INTENTIONALLY BLANK ISSUED: 20 JAN 2015 7-30 ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION SECTION 8 HANDLING AND MAINTENANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-1 Required Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2 Recording Time in Service . . . . . . . . . . . . . . . . . . . . . . . 8-2 Required Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-3 Preventive Maintenance by the Pilot . . . . . . . . . . . . . . . 8-4 Alterations to Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . 8-5 Ground Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-6 Parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7 Cabin Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-7 Engine Oil and Filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-8 Gearbox Oil and Filter . . . . . . . . . . . . . . . . . . . . . . . . . . 8-9 Hydraulic Fluid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-10 Air Filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-10 Compressor Rinse and Wash . . . . . . . . . . . . . . . . . . . . . 8-10 Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-11 Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-12 Cleaning Helicopter . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-13 ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-i INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-1 SECTION 8 HANDLING AND MAINTENANCE GENERAL This section outlines procedures recommended for handling, servicing, and maintaining the R66 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 R66 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. Authorized Robinson Service Centers will have recommended modification, service, and operating procedures issued by the FAA and by Robinson Helicopter Company. This information will be useful in obtaining maximum utility and safety with the helicopter. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 16 APR 2013 8-2 REQUIRED DOCUMENTS The Airworthiness Certificate (FAA form 8100-2) must be displayed in the aircraft at all times. The following additional documents must be carried in the aircraft: 1. Registration Certificate (FAA Form 8050-3) 2. Pilot’s Operating Handbook 3. Current Weight and Balance The following documents should not be carried in the aircraft, but must be available for use by any mechanic or pilot servicing the aircraft: 1. Aircraft Logbook 2. Engine Logbook NOTE Required documents may vary in countries other than the United States. RECORDING TIME IN SERVICE It is the operator’s responsibility to maintain a record of time in service for the engine, airframe, and all life-limited components, as well as the number of start cycles for the engine. Two hourmeters are provided: the hourmeter on the console records all run time including ground idle and is provided for reference. The hourmeter located outboard of the pilot’s seat is collective-activated and records run time only when the collective is raised off the down stop. The collective-activated hourmeter may be used to determine time in service for maintenance purposes, including time in service for all life-limited components. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-3 REQUIRED INSPECTIONS Federal Regulations require most civil aircraft of U.S. registry to undergo a complete inspection every twelve months. This annual inspection must be signed off by a mechanic with Inspection Authorization (lA). In addition to the annual inspection, the R66 Maintenance Manual requires a complete inspection after every 100 hours of operation. The helicopter incorporates a number of fatigue life-limited components which must be retired at specified time intervals. A list of these components is contained in the Airworthiness Limitations section of the R66 Maintenance Manual and Instructions for Continued Airworthiness. The engine also has life limits based on both time in service and start cycles. These limits are found in the RR300 Series Operation and Maintenance Manual (OMM). The R66 helicopter includes many unique features. Without special training, Airframe and Powerplant (A&P) mechanics are not qualified to perform the above inspections. These inspections must be performed only by properly rated personnel who have successfully completed a factory- approved maintenance course of instruction on the R66 helicopter. The factory occasionally publishes Service Bulletins and the Federal Aviation Administration (FAA) occasionally publishes Airworthiness Directives (ADs) that apply to specific groups of aircraft. They are mandatory changes or inspections which must be complied with within the time limit specified. Owners should periodically check with Robinson Service Centers to be sure that the latest Service Bulletins and ADs issued have been complied with. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-6 GROUND HANDLING For leveling, hoisting, or jacking, see appropriate sections of the maintenance manual. The helicopter may be maneuvered on the ground using ground handling wheels. Ground handling wheels are attached inboard of the landing gear skid tubes forward of the rear struts. Recommended tire pressure is 60 psi (4 bar). Wheels must be removed for flight. To attach wheels: 1. Hold handle and wheel with protruding spindle in its lowest position. 2. Insert spindle into support mounted on skid. Make sure spindle is all the way in. 3. Pull handle over center to raise helicopter and lock wheel in position. CAUTION When lowering helicopter, handle has a tendency to snap over. Ground handling generally requires two people: one to hold the tail down and steer by holding the tail rotor gearbox and a second to push on the fuselage. Keep feet clear of skid tubes. Alternately, a Robinson electric tow cart may be used per the instructions provided. CAUTION Do not move helicopter by gripping tail rotor guard, outboard part of horizontal stabilizer, tail rotor, or tail rotor controls. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-7 PARKING 1. Place cyclic control in neutral and apply friction. 2. Put collective full down and apply friction. 3. Align rotor blades approximately fore and aft. Apply rotor brake. Use blade tie-downs in windy conditions. CAUTION If using rotor blade tie-downs, do not overtighten tie-down straps (5 lb max tension). Do not pull down on blades to teeter rotor. To lower a blade, push up on opposite blade. 4. During storm conditions, helicopter should be hangared or moved to a safe area. CABIN DOORS All four cabin doors may be removed and installed by maintenance personnel or pilots. To remove a door, disconnect door strut by lifting inboard end of strut while holding door in full open position, remove cotter rings in upper and lower hinge pins, and then lift door off. To install doors, use reverse procedure. Adjust weight and balance as required when removing or installing doors. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-11 FUEL Approved fuel grades and capacity are given in Section 2. The aircraft should be electrically grounded prior to fueling. Grounding provisions are provided inside the fuel filler cowl door for a grounding clip or an M83413/4-1 style plug. Attach the ground cable before removing the filler cap. A quick drain located at the fuel tank low point is accessible via a cowl door on the left side of the aircraft. A small quantity of fuel should be drained using the quick drain prior to the first flight each day. Drain enough fuel to remove any water or contaminants. If fuel contamination is suspected, continue to drain fuel until all contamination is eliminated. The engine is equipped with a fuel filter. A switch at the filter illuminates the FUEL FILTER annunciator if the filter becomes contaminated. Fuel will continue to flow to the engine with a contaminated filter but may bypass the filter element. Refer to RR300 Series Operation and Maintenance Manual for filter servicing instructions. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-12 BATTERY The 24-volt battery is located in a compartment in the left side of the baggage compartment. The battery is sealed and does not require fluid level checks. A discharged battery is NOT AIRWORTHY because it will not have the reserve capacity to operate the electrical system should the charging system fail in flight. The battery may be charged using the external power receptacle located inside the right engine cowl door. For charging currents less than 10 amps, power connected to the receptacle will flow directly to the battery without the aircraft battery switch ON. Later aircraft have a special receptacle for the Batteryminder charger (Robinson part number MT990-1 for 120-volt AC power or MT990-2 for 240-volt AC power). Use of this charger will ensure a fully-charged battery and will maximize battery life. For information on battery replacement or capacity checks, see R66 Maintenance Manual. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-13 CLEANING HELICOPTER CLEANING EXTERIOR SURFACES The helicopter should be washed with mild soap and water. Harsh abrasives, alkaline soaps, or detergents could scratch painted or plastic surfaces or could cause corrosion of metal. Cover areas where cleaning solution could cause damage. Use the following procedure: 1. Rinse away loose dirt with water. 2. Apply cleaning solution with a soft cloth, sponge, or soft bristle brush. 3. To remove stubborn oil and grease, use a cloth dampened with aliphatic naphtha. 4. Rinse all surfaces thoroughly. 5. Any good automotive wax may be used to preserve painted surfaces. Soft cleaning cloths or a chamois should be used to prevent scratches when cleaning or polishing. CAUTION Never use high-pressure spray to clean helicopter. Never blow compressed air into main or tail rotor blade tip drain holes. CLEANING WINDSHIELD AND WINDOWS 1. Remove dirt, mud, and other loose particles from exterior surfaces with clean water. 2. Wash with mild soap and warm water or with aircraft plastic cleaner. Use a soft cloth or sponge in a straight back and forth motion. Do not rub harshly. 3. Remove oil and grease with a cloth moistened with isopropyl alcohol (rubbing alcohol) or aliphatic naphtha. ROBINSON MODEL R66 SECTION 8 HANDLING AND MAINTENANCE REVISED: 20 JAN 2015 8-14 CLEANING HELICOPTER (cont’d) CLEANING WINDSHIELD AND WINDOWS (cont’d) CAUTION Do not use gasoline, other alco- hols, benzene, carbon tetrachlo- ride, thinner, acetone, or window (glass) cleaning sprays. 4. After cleaning plastic surfaces, apply a thin coat of hard polishing wax. Rub lightly with a soft cloth. Do not use a circular motion. 5. Scratches can be removed by rubbing with jeweler’s rouge followed by hand polishing with commercial plastic polish. Use a figure eight motion when polishing. CLEANING UPHOLSTERY AND SEATS 1. Vacuum and brush, then wipe with damp cloth. Dry immediately. 2. Soiled upholstery, except leather, may be cleaned with a good upholstery cleaner suitable for the material. Follow manufacturer’s instructions. Avoid soaking or harsh rubbing. 3. Leather should be cleaned with saddle soap or a mild hard soap and water. CLEANING CARPETS Remove loose dirt with a whisk broom or vacuum. For soiled spots and stains, use nonflammable dry cleaning liquid. SECTION 9 SUPPLEMENTS OPTIONAL EQUIPMENT SUPPLEMENTS Information contained in the following supplements applies only when the related equipment is installed. CONTENTS Page Heated Pitot . . . . . . . . . . . . . . . . . . . . . . . 9-1.1 Air Conditioning . . . . . . . . . . . . . . . . . . . . 9-2.1 Pop-Out Floats . . . . . . . . . . . . . . . . . . . . . 9-3.1 Police Version . . . . . . . . . . . . . . . . . . . . . . 9-4.1 ADS-B Equipment . . . . . . . . . . . . . . . . . . . 9-5.1 Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . 9-6.1 NON-U.S. SUPPLEMENTS The following supplements contain additional information required by certain countries: Argentine Supplement Brazilian Supplement CIS Supplement Ukrainian Supplement ROBINSON MODEL R66 SECTION 9 SUPPLEMENTS FAA APPROVED: 20 JAN 2015 9-i INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT 9-3.1 FAA APPROVED R66 PILOT’S OPERATING HANDBOOK POP-OUT FLOATS SUPPLEMENT This supplement must be included in the FAA-approved Pilot’s Operating Handbook when pop-out floats are installed. Information contained herein supplements or supersedes the . t n e m e l p p u s s i h t n i d e t s il s a e r a e s o h t n i y l n o l a u n a m c i s a b For limitations, procedures, and performance information not contained in this supplement, consult the basic Pilot’s Operating Handbook. APPROVED BY: Manager, Flight Test Branch ANM-160L Federal Aviation Administration Los Angeles Aircraft Certification Office, Transport Airplane Directorate DATE: LOG OF PAGES Page No. Date 9-3.9 9-3.10 9-3.11 9-3.12 9-3.13 9-3.14* 9-3.15* 9-3.16* 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 * Manufacturer’s data, not FAA approved. Page No. Date 9-3.1 9-3.2* 9-3.3 9-3.4 9-3.5 9-3.6 9-3.7 9-3.8 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 14 Nov 2014 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT ISSUED: 14 NOV 2014 9-3.2 SECTION 1: GENERAL INTRODUCTION This supplement contains the changes and additional data applicable when pop-out floats are installed. Pop-out floats are intended for safety during over-water flights. Intentional water landings for other than training purposes are not recommended. Note: The pop-out floats are approved for amphibious operation but are not certified for ditching. Some countries may prohibit certain over-water operations. FAA APPROVED: 14 NOV 2014 9-3.3 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT SECTION 2: LIMITATIONS AIRSPEED LIMITS NEVER-EXCEED AIRSPEED (VNE) – FLOATS STOWED All Weights 130 KIAS Autorotation 100 KIAS For VNE reductions with altitude and temperature, see placards on page 9-3.5. ADDITIONAL AIRSPEED LIMITS 65 KIAS maximum above 83% torque. With floats stowed, 100 KIAS maximum with any combination of cabin doors removed. 80 KIAS maximum for float inflation. 80 KIAS maximum with floats inflated. ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT FAA APPROVED: 14 NOV 2014 9-3.4 SECTION 2: LIMITATIONS (cont’d) WEIGHT LIMITS Maximum weight for intentional water operations 2200 lb (998 kg) FLIGHT AND MANEUVER LIMITATIONS Maximum descent with floats inflated is 4000 feet. CAUTION Descents greater than 4000 feet may cause floats to lose shape and rigidity due to atmospheric pressure increase. Do not inflate floats above 4000 feet AGL. Water landings for any reason other than an actual emergency prohibited at weights above 2200 lb (998 kg). KINDS OF OPERATION LIMITATIONS Except for an actual emergency, night operation with floats inflated is prohibited. INSTRUMENT MARKINGS AIRSPEED INDICATOR Green arc 0 to 130 KIAS Red cross-hatch 100 KIAS Red line 130 KIAS FAA APPROVED: 14 NOV 2014 9-3.5 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT SECTION 2: LIMITATIONS (cont’d) PLACARDS Adjacent to pilot’s cyclic grip: Near inflation lever: DO NOT INFLATE FLOATS ABOVE 80 KIAS ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT FAA APPROVED: 14 NOV 2014 9-3.6 SECTION 3: EMERGENCY PROCEDURES POWER FAILURE – GENERAL CAUTION Lowering collective rapidly or applying excessive forward cyclic while helicopter is moving forward on water can cause floats to submerge and helicopter to nose over. POWER FAILURE ABOVE 500 FEET AGL Autorotation to land: Same as in basic manual. Autorotation to water: 1. Lower collective immediately to maintain rotor RPM. 2. Reduce airspeed to below 80 KIAS. 3. Adjust collective to keep RPM between 95 and 106% or apply full down collective if light weight prevents attaining above 95%. 4. If altitude permits, maneuver into wind. 5. Inflate floats. CAUTION Do not inflate floats above 80 KIAS. Do not exceed 80 KIAS with floats inflated. 6. At about 40 feet AGL, begin cyclic flare. 7. At about 8 feet AGL, apply forward cyclic and raise collective just before touchdown. Touch down in slight nose high attitude with nose straight ahead. 8. Maintain cyclic in touchdown position and do not lower collective full down until forward motion has stopped. FAA APPROVED: 14 NOV 2014 9-3.7 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT SECTION 3: EMERGENCY PROCEDURES (cont’d) POWER FAILURE BETWEEN 8 FEET AND 500 FEET AGL Autorotation to land: Same as in basic manual. Autorotation to water: 1. Lower collective immediately to maintain rotor RPM. 2. Reduce airspeed to below 80 KIAS. 3. Adjust collective to keep RPM between 95 and 106% or apply full down collective if light weight prevents attaining above 95%. 4. If altitude permits, maneuver into wind. 5. Inflate floats. CAUTION Do not inflate floats above 80 KIAS. Do not exceed 80 KIAS with floats inflated. CAUTION Float inflation may take up to three seconds. Squeeze lever early enough to allow full inflation before water contact. 6. Maintain airspeed until water is approached, then begin cyclic flare. 7. At about 8 feet AGL, apply forward cyclic and raise collective just before touchdown. Touch down in slight nose high attitude with nose straight ahead. 8. Maintain cyclic in touchdown position and do not lower collective full down until forward motion has stopped. ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT FAA APPROVED: 14 NOV 2014 9-3.8 SECTION 3: EMERGENCY PROCEDURES (cont’d) POWER FAILURE BELOW 8 FEET AGL Over land: Same as in basic manual. Over water: 1. Apply right pedal as required to prevent yawing. 2. Inflate floats. 3. Allow rotorcraft to settle. 4. Raise collective just before touchdown. MAXIMUM GLIDE DISTANCE CONFIGURATION Same as in basic manual except airspeed 80 KIAS with floats inflated. With floats inflated, best glide ratio is about 5.2:1 or one nautical mile per 1200 feet AGL. EMERGENCY WATER LANDING – POWER OFF See procedures for power failures in this supplement. EMERGENCY WATER LANDING – POWER ON 1. Reduce airspeed to below 80 KIAS. 2. Inflate floats. CAUTION Do not inflate floats above 80 KIAS. Do not exceed 80 KIAS with floats inflated. 3. Make normal approach and landing to water. FAA APPROVED: 14 NOV 2014 9-3.9 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT SECTION 4: NORMAL PROCEDURES DAILY OR PREFLIGHT CHECKS 9. Pop-Out Floats Check float and cover condition Check hose and fitting condition Check pressure in pressure cylinder Verify safety pin at pressure cylinder removed Set inflation lever safety READY or LOCKED as desired CAUTION Avoid night flight over water beyond autorotation distance to land. Height above water may be difficult to judge during a water landing. COLD WEATHER OPERATION When OAT is below -10°C, there may be insufficient charge in pressure cylinder for full float inflation. FLOAT INFLATION The red inflation lever located under the pilot’s collective is equipped with a safety to prevent inadvertent float inflation. Prior to overwater flight, push spring-loaded knob to left with thumb while rotating U-shaped catch from LOCKED to READY position with forefinger. With safety in READY position, floats may be inflated by squeezing inflation lever. Over land, safety should be reset to LOCKED position. ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT FAA APPROVED: 14 NOV 2014 9-3.10 SECTION 4: NORMAL PROCEDURES (cont’d) FLOAT INFLATION (cont’d) CAUTION The pressure cylinder is equipped with a safety pin at the valve. This safety pin is for use during maintenance and cylinder transport only and must be removed at all other times. CAUTION Helicopters equipped with inflated floats have an adverse roll characteristic. When sideslipping nose left or right, helicopter will tend to roll in opposite direction and could cause loss of control. To avoid adverse roll, keep helicopter trimmed with zero sideslip. Exercise extreme caution when performing simulated power failures. NOTE Some flapping of float covers during flight with floats inflated is normal. To minimize wear, consider removing covers if an extended flight with inflated floats is required. FAA APPROVED: 14 NOV 2014 9-3.11 ROBINSON MODEL R66 SECTION 9 POP-OUT FLOATS SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) OPERATION ON WATER Safe operation on water has been demonstrated in waves up to 1 foot (0.3 m) (trough to crest). Maximum recommended water taxi speed is 5 knots. Some application of collective is required. Since the helicopter sits very low on