Robinson Model R66 Section 9 FATA Supplement

SECTION 2: LIMITATIONS (cont’d) INSTRUMENT MARKINGS AIRSPEED INDICATOR (METRIC VERSION ONLY) Green arc 0 to 204 km/h (0 to 110 KIAS) Yellow arc* 204 to 259 km/h (110 to 140 KIAS) Red cross-hatch 185 km/h (100 KIAS) Red line 259 km/h (140 KIAS) *Earlier English units airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 110 KIAS EXCEPT IN SMOOTH AIR Earlier metric units airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 204 KM/H EXCEPT IN SMOOTH AIR FAA APPROVED: 21 NOV 2017 Page 9-F7.7 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 2: LIMITATIONS (cont’d) PLACARDS Adjacent to pilot’s cyclic grip: FAA APPROVED: 21 NOV 2017 Page 9-F7.8 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.9 SECTION 2: LIMITATIONS (cont’d) PLACARDS (cont’d) Adjacent to altimeter (on R66 helicopters equipped with an altimeter calibrated in feet only): ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 2: LIMITATIONS (cont’d) PLACARDS (cont’d) Near lock on rear cabin doors: НАЖАТЬ ДЛЯ БЛОКИРОВКИ НЕ БЛОКИРОВАТЬ НА ВРЕМЯ ПОЛЕТА (Push to lock Do not lock in flight) Inside cabin above each cabin door: ВЬІХОД (Exit) In clear view of all occupants: НЕ КУРИТЬ (No smoking) FAA APPROVED: 21 NOV 2017 Page 9-F7.10 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.11 SECTION 2: LIMITATIONS (cont’d) PLACARDS (cont’d) Inside each under-seat compartment: ОСТОРОЖНО НЕ ПРЕВЬІШАТЬ СЛЕДУЮЩИХ ОГРАНИЧЕНИЙ • МАКС. ВЕС БАГАЖА В ОТСЕКЕ: 23 КГ (50 ФУНТОВ) • МАКС. ВЕС ПАССАЖИРА С РАСПОЛОЖЕННЬІМ В ОТСЕКЕ БАГАЖОМ: 136 КГ (300 ФУНТОВ) • МАКС. УРОВЕНЬ ЗАПОЛНЕНИЯ ДОПОЛНИТЕЛЬНУЮ ИНФОРМАЦИЮ ПО ЗАГРУЗКЕ СМ. В РЛЭ (Caution Do not exceed any of the following: • Compartment capacity: 23 kg (50 lb) • Combined seat plus compartment: 136 kg (300 lb) • Max fill line See Pilot’s Handbook for additional loading instructions.) On or near collective controls: НЕ ЗАГРОМОЖДАТЬ ОСТАВЛЯТЬ МЕСТО СВОБОДНЬІМ (No stowage Keep area clear) ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 2: LIMITATIONS (cont’d) PLACARDS (cont’d) Near fuel tank filler cap: ТОПЛИВО: ТС-1, РТ ДРУГИЕ ТИПЬІ ТОПЛИВА СМ. В РЛЭ (Fuel: TS-1, RT See Pilot’s Handbook for other fuel types) Inside the baggage compartment: ОСТОРОЖНО МАКСИМАЛЬНАЯ РАСПРЕДЕЛЕННАЯ НАГРУЗКА НА ПОЛ: 244 КГ/М2 (50 ФУНТОВ/ФУТ2) МАКСИМАЛЬНЬІЙ ВЕС БАГАЖА: 136 КГ (300 ФУНТОВ) (Caution Maximum distributed floor load: 244 kg/m2 (50 lb/ft2) Maximum total compartment load: 136 kg (300 lb)) Inside each cabin door near door handle: ЗАКРЬІТЬ: СДВИНУТЬ РУЧКУ НАЗАД И ОИУСТИТЬ ОТКРЬІТЬ: ПОДНЯТЬ РУЧКУ И СДВИНУТЬ ВПЕРЕД (To close: Slide handle aft and down To open: Lift handle and slide forward) FAA APPROVED: 21 NOV 2017 Page 9-F7.12 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.13 SECTION 3: EMERGENCY PROCEDURES GENERAL NOTE The following procedures are unchanged from those of the basic manual. The only changes are that altitudes are converted to meters, and knots are converted to km/h. NOTE All speeds in km/h are indicated airspeed. ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 3: EMERGENCY PROCEDURES (cont’d) POWER FAILURE ABOVE 150 METERS (500 FEET) AGL 1. Lower collective immediately to maintain rotor RPM. 2. Establish a steady glide at approximately 130 km/h (70 KIAS). (For maximum glide distance or minimum rate of descent, see pages 9-F7.15 and 9-F7.16.) 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 12 meters (40 feet) AGL, begin cyclic flare to reduce rate of descent and forward speed. 8. At about 2.4 meters (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. FAA APPROVED: 21 NOV 2017 Page 9-F7.14 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.15 SECTION 3: EMERGENCY PROCEDURES (cont’d) POWER FAILURE BETWEEN 2.4 METERS (8 FEET) AND 150 METERS (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 2.4 meters (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 BELOW 2.4 METERS (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. MAXIMUM GLIDE DISTANCE CONFIGURATION 1. Airspeed approximately 165 km/h (90 KIAS). 2. Rotor RPM approximately 90%. Best glide ratio is about 5.5:1, or 1 km per 180 meters (one nautical mile per 1100 feet) AGL. ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 3: EMERGENCY PROCEDURES (cont’d) MINIMUM RATE OF DESCENT CONFIGURATION 1. Airspeed approximately 110 km/h (60 KIAS). 2. Rotor RPM approximately 90%. Minimum rate of descent is about 6.6 meters per second (1300 feet per minute). Glide ratio is about 4.5:1, or 1 km per 220 meters (one nautical mile per 1350 feet) AGL. CAUTION Increase rotor RPM to 95% minimum or full down collective when autorotating below 150 meters (500 feet) AGL. 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 130 km/h (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 130 km/h (70 KIAS); however, prior to reducing airspeed, enter full autorotation. FAA APPROVED: 21 NOV 2017 Page 9-F7.16 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.17 SECTION 4: NORMAL PROCEDURES GENERAL Icing conditions are indicated by the accumulation of ice at the tips of the landing gear skids, landing gear struts, and yaw strings. An increase in torque required to maintain airspeed is also an indication of icing conditions. Immediately leave suspected icing conditions by reversing track or landing as soon as possible. NOTE The following procedures are unchanged from those of the basic manual. The only changes are that altitudes are converted to meters, and knots are converted to km/h. NOTE All speeds in km/h are indicated airspeed. RECOMMENDED AIRSPEEDS Takeoff and Climb 111 km/h (60 KIAS) Maximum Range 185 km/h (100 KIAS)* Maximum Cruise 204 km/h (110 KIAS)* (Do not exceed except in smooth air, and then only with caution.) Significant Turbulence 111 to 130 km/h (60 to 70 KIAS) Landing Approach 111 km/h (60 KIAS) Autorotation 111 to 130 km/h (60 to 70 KIAS) *Certain conditions may require lower airspeed. See Vne placard in Section 2 of this supplement. ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) COLD WEATHER OPERATION Avionics equipment may not function, or function improperly, after a rotorcraft cold soak. Warm up the cabin to pass avionics self-test successfully. APPROVED FUEL GRADES TC-1 grade aviation fuel (GOST10227 specification) PT grade aviation fuel (GOST10227 specification) APPROVED FUEL ADDITIVES И grade aviation fuel additive (Fluid I) ИM grade aviation fuel additive (Fluid IM) FAA APPROVED: 21 NOV 2017 Page 9-F7.18 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) CRUISE 1. Beep RPM as required to 100%. 2. Set torque as desired with collective. Observe torque, MGT, and airspeed limits. Maximum recommended cruise speed is 204 km/h (110 KIAS). 3. Verify gages in green, no cautions or warnings. 4. Engine anti-ice as required. CAUTION Do not exceed 204 km/h (110 KIAS) except in smooth air and then only with caution. If turbulence is significant or becomes uncomfortable for the pilot, use 111 to 130 km/h (60 to 70 KIAS). DOORS-OFF OPERATION Maximum airspeed with any doors off is 185 km/h (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 doors-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. NOTE Door removal on opposite sides of aircraft allows cross flow in cabin and increases noise levels. FAA APPROVED: 21 NOV 2017 Page 9-F7.19 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) PRACTICE AUTOROTATION – POWER RECOVERY CAUTION Verify a recent N1 deceleration check was performed prior to conducting autorotations. Do not close throttle above 3048 meters (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. Airspeed 111 km/h to 130 km/h (60 to 70 KIAS). 4. At about 12 meters (40 feet) AGL, begin cyclic flare to reduce rate of descent and forward speed and roll throttle smoothly on to recover engine power. 5. At about 2.4 meters (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 300 meters (1000 feet) of altitude. CAUTION If entering autorotation with a rapid collective input, close throttle before lowering 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 of this supplement. FAA APPROVED: 21 NOV 2017 Page 9-F7.20 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) DESCENT, APPROACH, AND LANDING 1. Reduce power with collective as desired. Observe airspeed limits. Maximum recommended airspeed is 204 km/h (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 111 km/h (60 KIAS). 3. Reduce airspeed and altitude smoothly to hover. (Be sure rate of descent is less than 1.5 meters per second (300 feet per minute) before airspeed is reduced below 56 km/h (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 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. FAA APPROVED: 21 NOV 2017 Page 9-F7.21 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 4: NORMAL PROCEDURES (cont’d) 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 600 meters (2000 feet) AGL. 2. Avoid blade slap. Blade slap generally occurs at airspeeds below 185 km/h (100 KIAS). It can usually be avoided by maintaining 185 km/h (100 KIAS) until rate of descent is over 5 meters per second (1000 feet per minute), then using a fairly steep approach until airspeed is below 120 km/h (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 150 meters (500 feet) AGL and preferably above 300 meters (1000 feet) AGL. 4. Repetitive noise is far more irritating than a single occurrence. If you must fly over the same area more than once, vary your flight path to not overfly the same buildings each time. 5. When overflying populated areas, look ahead and select the least noise-sensitive route. NOTE Above procedures do not apply where they would conflict with Air Traffic Control clearances or when, in the pilot’s judgment, they would result in an unsafe flight path. FAA APPROVED: 21 NOV 2017 Page 9-F7.22 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE GENERAL Hover controllability has been demonstrated in 31 km/h (17 knot) wind from any direction up to 3350 meters (11,000 feet) density altitude. Refer to hover performance charts for allowable gross weight. Maximum wind speed for operations near the ground and during engine start and shutdown is 46 km/h (25 kts). Indicated airspeed (km/h) shown on charts assumes zero instrument error. CAUTION Performance data presented in this section was obtained under ideal conditions. Performance under other conditions may be substantially less. USE OF CHARTS POWER ASSURANCE CHART The power assurance chart shows maximum allowable MGT at a specified torque. If the observed MGT is greater than indicated by the chart, the engine may not produce the power necessary to achieve the performance data given in this section without exceeding MGT limits. A power assurance check may be done in a hover or in forward flight and should be performed at the maximum practical power for best accuracy. The chart assumes no generator load and stabilized conditions. Temperature stabilization may take up to two minutes. Generator load should be minimal or the generator may be switched OFF during the check. An example on the chart shows correct use. FAA APPROVED: 21 NOV 2017 Page 9-F7.23 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) USE OF CHARTS (cont’d) POWER ASSURANCE CHART (cont’d) The chart may also be read in reverse, giving the minimum allowable torque at a specified MGT. It may be useful to use the chart to predict the torque available at MGT limits for a given pressure altitude and OAT. NOTE All speeds in km/h are indicated airspeeds. HOVER PERFORMANCE In-ground-effect (IGE) and out-of-ground-effect (OGE) hover performance is given in the Hover Ceiling vs. Gross Weight charts in this supplement. Note that hover performance is limited by the MGT five-minute limit, not by torque. Hover performance is substantiated up to 3350 meters (11,000 feet) density altitude; however, data is presented beyond 3350 meters (11,000 feet) density altitude only to determine performance with engine anti-ice, cabin heat, and/or generator loads over 50 amps. With anti-ice and cabin heat OFF, maximum IGE hover gross weight is 1225 kg (2700 lb) up to 3350 meters (11,000 feet) density altitude at any OAT within limits. To correct for anti-ice, cabin heat, and/or high generator load, increase the actual OAT as specified on the charts. The following example illustrates the calculation of an effective OAT when anti-ice and cabin heat are turned ON, and there is a 90-amp generator load (40 amps over the 50-amp load on which the charts are based). FAA APPROVED: 21 NOV 2017 Page 9-F7.24 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) USE OF CHARTS (cont’d) HOVER PERFORMANCE (cont’d) Pressure altitude: 2750 meters (9000 feet) Actual OAT: 0°C Anti-ice ON correction: 10°C Cabin heat ON correction: 20°C 90-amp load correction: (90 – 50)/20 = 2°C Effective OAT: 0 + 10 + 20 + 2 = 32°C A pressure altitude of 2750 meters (9000 feet) and OAT of 32°C are therefore used with the charts, giving a maximum gross weight of 1170 kg (2580 lb) for IGE hover and 1050 kg (2320 lb) for OGE hover. CLIMB PERFORMANCE Climb performance charts are given for maximum gross weight (1225 kg (2700 lb)) and for 1000 kg (2200 lb) gross weight at 111 km/h (60 KIAS) climb indicated airspeed and maximum continuous torque or MGT (whichever is less). Each chart gives the potential reduction in climb rate due to anti-ice and cabin heat. The charts assume a 50-amp generator load; generator load has a small effect on climb rate. Note that predicted climb rate is approximate; variations in aircraft and operating conditions may significantly affect performance. FAA APPROVED: 21 NOV 2017 Page 9-F7.25 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) USE OF CHARTS (cont’d) HEIGHT-VELOCITY DIAGRAM The height-velocity diagram is given for maximum gross weight at sea level and at 2380 meters (7800 feet) density altitude. An appropriate curve for altitudes between sea level and 2380 meters (7800 feet) may be used by interpolation. For example, a curve with a hover point at 183 meters (600 feet) AGL may be used for 1190 meters (3900 feet) density altitude. FAA APPROVED: 21 NOV 2017 Page 9-F7.26 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.27 SECTION 5: PERFORMANCE (cont’d) AIRSPEED CALIBRATION CURVE ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) DENSITY ALTITUDE CHART FAA APPROVED: 21 NOV 2017 Page 9-F7.28 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.29 SECTION 5: PERFORMANCE (cont’d) POWER ASSURANCE CHART ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) IGE HOVER CEILING VS. GROSS WEIGHT NOTE: Hover performance substantiated up to 3350 meters density altitude. Data is presented only to determine performance with engine anti-ice, cabin heat and/or generator loads over 50 amps. FAA APPROVED: 21 NOV 2017 Page 9-F7.30 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.31 SECTION 5: PERFORMANCE (cont’d) OGE HOVER CEILING VS. GROSS WEIGHT * Hover performance substantiated up to 3350 meters density altitude. Data beyond ISA + 35ºC and above 3350 meters density altitude is presented only to determine performance with engine anti-ice, cabin heat, and/or generator loads over 50 amps. ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) CLIMB PERFORMANCE, 1225 KG GROSS WEIGHT FAA APPROVED: 21 NOV 2017 Page 9-F7.32 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.33 SECTION 5: PERFORMANCE (cont’d) CLIMB PERFORMANCE, 1000 KG GROSS WEIGHT ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 5: PERFORMANCE (cont’d) DEMONSTRATED CONDITIONS: SMOOTH HARD SURFACE WIND CALM 1225 KG GROSS WEIGHT HOVER POWER + 10% TORQUE FOR TAKEOFF HEIGHT – VELOCITY DIAGRAM FAA APPROVED: 21 NOV 2017 Page 9-F7.34 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.35 SECTION 5: PERFORMANCE (cont’d) NOISE CHARACTERISTICS The following noise levels comply with 14 CFR Part 36, Appendix H and ICAO Annex 16, Volume 1, Chapter 8 noise requirements and were obtained from FAA- approved data from actual noise tests. Model: R66 Engine: Rolls-Royce Model 250-C300/A1 Gross Weight: 1225 kg Configuration Vh KM/H True Airspeed Noise Level (EPNdB) Flyover Takeoff Approach Clean 217 84.5 87.8 87.8 Dirty* 200 84.8 87.8 88.6 * Landing gear strut fairings removed. Air conditioning and four doors with bubble windows installed. NOTE No determination has been made by the Certifying Authority that the noise levels are or should be acceptable or unacceptable for operation at, into, or out of any airport. ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 6: WEIGHT AND BALANCE No change. SECTION 7: SYSTEMS DESCRIPTION FIRST-AID KIT A first-aid kit (supplied by operator) should be stored in the accessory box located in front of the forward left seat. SECTION 8: HANDLING, SERVICING AND MAINTENANCE No change. FAA APPROVED: 21 NOV 2017 Page 9-F7.36 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.37 SECTION 9: SUPPLEMENTS HEATED PITOT SUPPLEMENT No change. AIR CONDITIONING SUPPLEMENT SECTION 5: PERFORMANCE CLIMB PERFORMANCE, 2700 LB (1225 KG) GROSS WEIGHT Air conditioning operation may reduce climb rate up to 0.25 meters/second (50 ft/min). CLIMB PERFORMANCE, 2200 LB (998 KG) GROSS WEIGHT Air conditioning operation may reduce climb rate up to 0.30 meters/second (60 ft/min). ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 9: SUPPLEMENTS POP-OUT FLOATS SUPPLEMENT SECTION 2: LIMITATIONS AIRSPEED LIMITS NEVER-EXCEED AIRSPEED (VNE) – FLOATS STOWED All Weights 241 km/h (130 KIAS) Autorotation 185 km/h (100 KIAS) For VNE reductions with altitude and temperature, see placards on page 9-F7.40. ADDITIONAL AIRSPEED LIMITS 120 km/h (65 KIAS) maximum above 83% torque. With floats stowed, 185 km/h (100 KIAS) maximum with any combination of cabin doors removed. 148 km/h (80 KIAS) maximum for float inflation. 148 km/h (80 KIAS) maximum with floats inflated. 213 km/h (115 KIAS) maximum with float system armed (safety catch in READY position). FAA APPROVED: 21 NOV 2017 Page 9-F7.38 ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT FAA APPROVED: 21 NOV 2017 Page 9-F7.39 SECTION 9: SUPPLEMENTS (cont’d) POP-OUT FLOATS SUPPLEMENT (cont’d) SECTION 2: LIMITATIONS (cont’d) FLIGHT AND MANEUVER LIMITATIONS Maximum altitude decrease with floats inflated is 1220 meters (4000 feet). CAUTION Altitude loss greater than 1220 meters (4000 feet) may cause floats to lose shape and rigidity due to atmospheric pressure increase. Do not inflate floats above 1220 meters (4000 feet) AGL. Flights over water beyond safe auto-rotation distance from land are prohibited after a cold soak below 0°C or in ambient temperatures below 0°C. Duration of pop-out floats usage on water must not exceed 6 hours. INSTRUMENT MARKINGS AIRSPEED INDICATOR (METRIC VERSION ONLY) Green arc 0 to 204 km/h (0 to 110 KIAS) Yellow arc* 204 to 241 km/h (110 to 130 KIAS) Red cross-hatch 185 km/h (100 KIAS) Red line 241 km/h (130 KIAS) *Earlier English units airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 110 KIAS EXCEPT IN SMOOTH AIR Earlier metric units airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 204 KM/H EXCEPT IN SMOOTH AIR ROBINSON MODEL R66 SECTION 9 FATA SUPPLEMENT SECTION 9: SUPPLEMENTS (cont’d) POP-OUT FLOATS SUPPLEMENT (cont’d) SECTION 2: LIMITATIONS (cont’d) PLACARDS Adjacent to pilot’s cyclic grip on helicopters equipped with a metric altimeter and airspeed indicator: Near inflation lever on helicopters equipped with a metric airspeed indicator: DO NOT INFLATE FLOATS ABOVE 148 km/h (80 KIAS) FAA APPROVED: 21 NOV 2017 Page 9-F7.40