R66 Pilot's Operating Handbook

responsible for determining that the helicopter is safe for flight. The pilot is also responsible for remaining within operating limitations as outlined by instrument markings, placards, and this handbook. Since it is very difficult to refer to a handbook while flying a helicopter, the pilot should study the entire handbook and become very familiar with limitations, performance, procedures, and operational handling characteristics of the helicopter before flight. This handbook has been divided into ten numbered sections. Limitations and emergency procedures have been placed ahead of normal procedures, performance, and other sections to provide easier access to that information. Provisions for expansion of the handbook have been made by deliberate omission of certain paragraph numbers, figure numbers, item numbers, and pages noted as being intentionally blank. ISSUED: 25 OCT 2010 1-1 ROBINSON MODEL R66 CAUTIONS AND NOTES SECTION 1 GENERAL Cautions and Notes emphasize important information and are used as follows: CAUTION Equipment damage, injury, or death can result if procedure or instruction is not followed. NOTE Provides emphasis or supplementary infor- mation. ISSUED: 25 OCT 2010 1-2 ROBINSON MODEL R66 SECTION 1 GENERAL REVISED: 15 AUG 2023 1-3 R66 EXTERNAL DIMENSIONS (LATER AIRCRAFT SHOWN) EXTERNAL DIMENSIONS ROBINSON MODEL R66 SECTION 1 GENERAL ISSUED: 25 OCT 2010 1-4 DESCRIPTIVE DATA MAIN ROTOR Articulation Free to teeter and cone, rigid in plane Number of Blades 2 Diameter 33 feet Blade Chord 11.5 inches inboard, 12.2 inches outboard Blade Twist -4 Degrees Tip Speed at 100% RPM 705 feet per second TAIL ROTOR Articulation Free to teeter, rigid in plane Number of Blades 2 Diameter 60 inches Blade Chord 5.5 inches (constant) Blade Twist 0 Precone Angle 1 Degree Tip Speed at 100% RPM 635 feet per second DRIVE SYSTEM Engine to Drive Line Sprag type overrunning clutch, spiral-bevel gears with 13:37 speed reducing ratio Drive Line to Main Rotor Spiral-bevel gears with 11:57 speed reducing ratio Drive Line to Tail Rotor Spiral-bevel gears with 31:27 speed increasing ratio ROBINSON MODEL R66 DESCRIPTIVE DATA (cont'd) POWER PLANT Model: Rolls-Royce 250-C300/A 1 commercial designation RR300 (FAA type certificate no. E4CE) Type: Free-turbine turboshaft Manufacturer's rating: 300 SHP R66 5 minute takeoff rating: 270 SHP R66 continuous rating: 224 SHP FUEL SECTION 1 GENERAL Approved fuel grades and capacity: See Section 2. OIL Approved oil grades and capacity: See Section 8. ISSUED: 25 OCT 2010 1-5 ROBINSON MODEL R66 SECTION 1 GENERAL PERFORMANCE DEFINITIONS KIAS KCAS KTAS Knots Indicated Airspeed is speed shown on the airspeed indicator. Knots Calibrated Airspeed is speed shown on the airspeed indicator corrected for instrument and position error. (See Section 5 for position error correction.) Knots True Airspeed is airspeed relative to un- disturbed air. It is KCAS corrected for pressure altitude and temperature. Never-Exceed Airspeed. Vv Speed for best rate of climb. Vh Stabilized level-flight speed at maximum continuous power. MSL Altitude Pressure Altitude Density Altitude ISA SHP Altitude above mean sea level, indicated by the altimeter (corrected for position and instrument error) when the barometric subscale is set to the atmospheric pressure existing at sea level. Altitude indicated by the altimeter (corrected for instrument error) when the barometric sub- scale is set to 29.92 inches of mercury (1013.2mb). Altitude in ISA conditions at which the air would have the same density (it is pressure altitude corrected for OAT). International Standard Atmosphere exists when pressure is 29.92 inches of mercury at sea level, temperature is 15°C at sea level, and temperature decreases 1 .98 °C per 1000 feet of altitude. Shaft Horsepower is actual power delivered by the engine output shaft. (Shown by torque meter as percentage of 270 horse- power when N2 is 100%). ISSUED: 25 OCT 2010 1-6 ROBINSON MODEL R66 PERFORMANCE DEFINITIONS (cont'd) SECTION 1 GENERAL RPM Revolutions Per Minute or speed of engine or rotor. Shown on R66 tachometers in percent. 100% engine output shaft (N 2 ) RPM = 6016. 100% gas generator (N 1) RPM = 50970. 100% main rotor RPM = 408. N 1 Engine gas generator (compressor) RPM. N 2 Engine output shaft RPM. MGT Measured Gas Temperature (in turbine section). MCP Maximum Continuous Power (83% torque in the R66). TOP Takeoff Power ( 100% torque, limited to 5 minutes in the R66). TOGW Takeoff Gross Weight. OAT Outside Air Temperature. GPH Gallons Per Hour. AGL Above Ground Level. IGE In Ground Effect. OGE Out of Ground Effect. ISSUED: 25 OCT 2010 1-7 ROBINSON MODEL R66 SECTION 1 GENERAL WEIGHT AND BALANCE DEFINITIONS Reference Datum Station Arm Moment Center of Gravity (CG) CG Limits Usable Fuel Unusable Fuel A vertical plane from which horizontal dis- tances are measured for balance purposes. The longitudinal reference datum is 1 00 inches forward of the main rotor shaft centerline for the R66. Fore-and-aft location along the helicopter fuselage given in terms of distance in inches from the longitudinal reference datum. Horizontal distance from a reference datum to the center of gravity (CG) of an item. The weight of an item multiplied by its arm. Location on the fuselage (usually expressed in inches from the reference datum) at which the helicopter would balance. CG is calcula- ted by dividing total helicopter moment by total helicopter weight. Extreme CG locations within which the heli- copter must be operated at a given weight. Fuel available for flight planning. Fuel remaining in the tank that cannot reliably provide uninterrupted fuel flow in the critical flight attitude. Standard Weight of a standard helicopter including Empty Weight unusable fuel, full operating fluids, and full engine oil. Basic Empty Weight Payload Useful Load Standard empty weight plus weight of in- stalled optional equipment. Weight of occupants, cargo, and baggage. Difference between maximum gross weight and basic empty weight. ISSUED: 25 OCT 2010 1-8 ROBINSON MODEL R66 CONVERSION TABLES METRIC TO ENGLISH Multiply centimeters (cm) kilograms (kg) kilometers (km) kilometers (km) liters (I) liters (I) meters (m) ENGLISH TO METRIC Multiply feet (ft) gallons, U.S. (gal) inches (in) inches (in) nautical miles (nm) pounds (lb) quarts (qt) statute miles (mi) ~ 0.3937 2.2046 0.5400 0.6214 0.2642 1.0567 3.2808 ~ 0.3048 3.7854 2.5400 25.4000 1.8520 0.4536 0.9464 1.6093 SECTION 1 GENERAL To Obtain inches (in) pounds (lb) nautical miles (nm) statute miles (mi) gallons, U.S. (gal) quarts (qt) feet (ft) To Obtain meters (m) liters (I) centimeters (cm) millimeters (mm) kilometers (km) kilograms (kg) liters (I) kilometers (km) 1 nautical mile = 1 . 1 508 statute miles 1 statute mile = 0.8690 nautical mile TEMPERATURE °F = 9/5 (°C)+32 °C = 5/9 (°F - 32) ISSUED: 25 OCT 2010 1-9 ROBINSON MODEL R66 THIS PAGE INTENTIONALLY BLANK ISSUED: 25 OCT 2010 SECTION 1 GENERAL 1-10 SECTION 2 LIMITATIONS CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Color Code for Instrument Markings . . . . . . . . . . . . . . . 2-1 Airspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Rotor Speed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 Powerplant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . 2-2 Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Flight and Maneuver Limitations . . . . . . . . . . . . . . . . . . 2-5 Kinds of Operation Limitations . . . . . . . . . . . . . . . . . . . . 2-6 Environmental Limitations . . . . . . . . . . . . . . . . . . . . . . . 2-6 Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7 Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-i INTENTIONALLY BLANK SECTION 2 LIMITATIONS GENERAL This section includes operating limitations, instrument markings, and basic placards required for safe operation of the helicopter, its engine, and other standard systems. This helicopter is approved as a normal category rotorcraft under FAA Type Certificate No. R00015LA as Model R66. COLOR CODE FOR INSTRUMENT MARKINGS Red Operating limit. Edge of red line indicates limit. Pointer should not enter red during normal operation. Red Cross- Hatch Power-off Vne . Yellow Precautionary or special operating procedure range. Green Normal operating range. AIRSPEED LIMITS NEVER-EXCEED AIRSPEED (V ne ) 2200 lb (998 kg) TOGW or above 130 KIAS Below 2200 lb (998 kg) TOGW 140 KIAS Autorotation 100 KIAS For Vne reductions with altitude and temperature, see placards on page 2-10. ADDITIONAL AIRSPEED LIMITS 65 KIAS maximum above 83% torque. 100 KIAS maximum with any combination of cabin doors removed. FAA APPROVED: 19 OCT 2016 2-1 ROBINSON MODEL R66 SECTION 2 LIMITATIONS ROTOR SPEED LIMITS Power On Maximum continuous 101% (412 RPM) Minimum continuous 99% (404 RPM) Power Off Maximum 106% (432 RPM) Minimum 88% (359 RPM) POWERPLANT LIMITATIONS ENGINE One Rolls-Royce Model 250-C300/A1 OPERATING LIMITS Gas generator speed (N1) Maximum 105 % (53,519 RPM) Output shaft speed (N2) Maximum continuous 101 % (6076 RPM) Minimum continuous power on 99 % (5956 RPM) Maximum transient overspeed* 106 % (6377 RPM) Measured Gas Temperature (MGT) 5 minute limit Continuous limit Transient limit Limit during start 782 706 843 927 °C °C °C °C (6 seconds) (10 seconds) Torque 5 minute limit 100 % (236 lb-ft) Continuous limit 83 % (196 lb-ft) * Avoid large, rapid power changes. The engine governor reacts slowly and RPM excursions may occur. Intentional operation outside continuous RPM limits is prohibited. ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 21 JUN 2021 2-2 ROBINSON MODEL R66 SECTION 2 LIMITATIONS POWERPLANT LIMITATIONS (cont’d) OPERATING LIMITS (cont’d) Oil Temperature, Maximum 107°C Oil Pressure Maximum during start and warm up 150 psi Maximum operating 130 psi Minimum above 94% N1 115 psi Minimum below 78% N1 50 psi Minimum from 78% to 94% N1 90 psi Oil Quantity, minimum for takeoff 4 qt (3.8 liters) WEIGHT LIMITS Maximum gross weight 2700 lb (1225 kg) Minimum gross weight 1400 lb (635 kg) Maximum per seat including under-seat compartment 300 lb (136 kg) Maximum in any under-seat compartment 50 lb (23 kg) Baggage Compartment Maximum distributed load 50 lb/ft2 (244 kg/m2) Maximum total load 300 lb (136 kg) CENTER OF GRAVITY LIMITS See figure on page 2-4. Reference datum is 100 inches forward of main rotor shaft centerline. NOTE With all doors installed and no load in baggage compartment, a solo pilot weight of 160 lb (73 kg) or greater will ensure CG within limits. For lower pilot weight, compute weight and balance; removable ballast may be required to obtain CG at or forward of aft limit. (See Loading Instructions in Section 6.) FAA APPROVED: 26 NOV 2013 2-3 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 6 JUL 2018 2-4 CENTER OF GRAVITY LIMITS FUSELAGE STATION (IN . FROM DATUM) 00 ~ ~ ~ M ~ % ~ 00 ~ 1001~ 1~1ro 2800 . 1250 2700 2600 ) I "I f I ~ 1200 1150 2500 2400 m 2300 ...J ~ MOST FWD CG WITH "-.... '-.... FULL FUEL TO KEEP 1100 1050 (!J lo: I- 2200 :c (!J iii 2100 ;: CG WITHIN LIMITS AT ZERO FUEL. 1000 I- :c (!J iii 950 ;: C/l C/l 2000 0 IC (!J 1900 C/l C/l 900 0 IC (!J 850 1800 800 1700 750 1600 700 1500 1400 650 ~ MAIN ROTOR 4 R 10 R 3 R ~ -.... ... 8 R 6 R 2 R ~ 4 R :; () 1 R (!J 2 R (!J () ~ ...J ct () 0 ...J ct IC w 1 L I- 2 L IC w I- ct ...J 2 L 4 L ct ...J 3 L ~~ - 6 L 8 L 4 L . . 10 L 232 236 240 244 248 252 256 260 FUSELAGE STATION (CM FROM DATUM) ROBINSON MODEL R66 SECTION 2 LIMITATIONS FLIGHT AND MANEUVER LIMITATIONS Aerobatic flight prohibited. CAUTION Abrupt control inputs may produce high fatigue stresses and cause catastrophic failure of a critical component. Low-G cyclic pushovers prohibited. CAUTION A pushover (forward cyclic maneuver) performed from level flight or following a pull-up causes a low-G (near weightless) condition which can result in catastrophic loss of lateral control. To eliminate a low-G condition, immediately apply gentle aft cyclic. Should a roll commence during a low-G condition, apply gentle aft cyclic to reload rotor before applying lateral cyclic to stop roll. Maximum operating density altitude 14,000 feet. Maximum operating altitude 9000 feet AGL to allow landing within 5 minutes in case of fire. Closing throttle (twist grip) in flight prohibited above 10,000 feet density altitude to avoid possible engine flameout. Closing throttle (twist grip) in flight prohibited with cabin heat ON to avoid possible engine flameout. Minimum crew is one pilot in the right front seat. A flight instructor may act as pilot in command from the left front seat. Solo flight from right seat only. Forward left seat belt must be buckled. Operation up to 100 KIAS approved with any combination of cabin doors removed. All seat belts must be buckled and loose items in cabin must be properly secured during doors- off flight. A functioning headset must be worn by each pilot. FAA APPROVED: 15 AUG 2023 2-5 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 2 DEC 2015 2-6 KINDS OF OPERATION LIMITATIONS VFR day and night operations are approved. VFR operation at night is permitted only when landing, navigation, instrument, and anti-collision lights are operational. Orientation during night flight must be maintained by visual reference to ground objects illuminated solely by lights on the ground or adequate celestial illumination. NOTE There may be additional requirements in countries outside the United States. ENVIRONMENTAL LIMITATIONS Maximum ambient temperature for operation is ISA plus 35°C (ISA plus 63°F), limited to 50°C (122°F). Minimum ambient temperature for operation is -40°C (-40°F) at all altitudes. NOTE See fuel limitations for temperature restrictions. Flight in known icing conditions prohibited. 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 A-1 (ASTM D1655) Anti-icing additive may be required (see below). Not approved for ambient tem- peratures below –32ºC (–25ºF). Jet B (ASTM D6615) 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 6537-2006) Anti-icing additive may be required (see below). Not approved for ambient tem- peratures below –32ºC (–25ºF). TC-1 or PT (Russian Standard GOST 10227) No temperature restrictions. Aviation fuel additives grades И (Fluid I) and ИM (Fluid IM) with a concentration of 0.1 – 0.3% by volume are approved for anti-icing. Anti-icing additive conforming to MIL-DTL-85470 must be added to Jet A, Jet A-1, 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: 21 JUN 2021 2-7 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-8 INSTRUMENT MARKINGS NOTE Red lines offset so instrument pointer should not enter red. See color code on page 2-1. AIRSPEED INDICATOR Green arc 0 to 110 KIAS Yellow arc* 110 to 140 KIAS Red cross-hatch 100 KIAS Red Line 140 KIAS *Earlier airspeed indicators without yellow arc must have the following placard adjacent: DO NOT EXCEED 110 KIAS EXCEPT IN SMOOTH AIR ROTOR TACHOMETER Lower red line 88% Green arc 88 to 106% Upper red line 106% ENGINE TACHOMETER (N2) Yellow arc 75 to 88%** Power on – transient operation only. (No restrictions during autorotation.) Lower red line 99% Green arc 99 to 101% Upper red line 101% **Earlier tachometers with yellow arc from 78 to 88% must have the following placard adjacent: TRANSIENT OPERATION ONLY 75–88% N2 NO RESTRICTIONS DURING AUTOROTATION GAS PRODUCER TACHOMETER (N1) Green arc 60 to 105% Red line 105% White triangle 16% (Later tachometers. Recommended fuel ON during normal start) INSTRUMENT MARKINGS (cont’d) 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% N1 ) 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 TORQUE Green arc 0 to 83% Yellow arc (5 minute limit) 83 to 100% Red line 100% AMMETER Green arc 0 to 160 amps Red line 160 amps ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-9 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-10 PLACARDS Adjacent to pilot’s cyclic grip: Near fuel tank filler cap: FUEL GRADE JET A, JET A1, JET B OR AS SPECIFIED IN PILOT’S HANDBOOK ANTI-ICE ADDITIVE MAY BE REQUIRED SEE PILOT’S HANDBOOK POWER-ON Vne- KIAS PRESS OAT-°C ALT-FT -40 -30 -20 -10 0 10 20 30 40 50 SL 129 I 127 2000 124 130 126 122 4000 119 127 129 125 121 117 114 6000 114 122 125 121 117 113 108 8000 109 117 121 116 112 107 102 97 10000 105 112 112 106 101 96 91 86 12000 100 106 101 95 90 14000 96 95 89 NO FLIGHT 16000 90 BELOW 2200 LB (998 KG) TOGW, ADD 10 KIAS NOTE: 65 KIAS MAXIMUM ABOVE 83% TORQUE AUTOROTATION Vne - KIAS PRESS OAT-°C ALT-FT -40 -30 -20 -10 0 10 20 30 40 I 50 6000 I 8000 100 99 94 89 10000 98 93 88 83 78 12000 98 93 87 82 14000 93 87 81 NO FLIGHT 16000 82 PLACARDS (cont’d) Near fuel gage: 73.6 US GAL 279 LITERS In clear view of pilot: SEE PILOT’S HANDBOOK FOR SOLO PILOT WEIGHT LESS THAN 160 LB (73 KG) THIS ROTORCRAFT APPROVED FOR DAY AND NIGHT VFR OPERATIONS LOW-G PUSHOVERS PROHIBITED On removable cyclic grip: SOLO FROM RIGHT SEAT ONLY On or near collective controls: NO STOWAGE KEEP AREA CLEAR In clear view of all occupants: NO SMOKING Inside cabin above each cabin door: EXIT Inside each cabin door near door handle: TO CLOSE: SLIDE HANDLE AFT AND DOWN TO OPEN: LIFT HANDLE AND SLIDE FORWARD ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-11 ROBINSON MODEL R66 SECTION 2 LIMITATIONS FAA APPROVED: 19 OCT 2016 2-12 PLACARDS (cont’d) Near lock on rear cabin doors: PUSH TO LOCK DO NOT LOCK IN FLIGHT Inside each under-seat compartment: CAUTION DO NOT EXCEED THE FOLLOWING: • COMPARTMENT CAPACITY: 50 LB (23 KG) • COMBINED SEAT PLUS COMPARTMENT: 300 LB (136 KG) • MAX FILL LINE SEE PILOT’S HANDBOOK FOR ADDITIONAL LOADING INSTRUCTIONS. Inside main baggage compartment: CAUTION • MAXIMUM DISTRIBUTED FLOOR LOAD: 50 LB/FT2 (244 KG/M2 ) • MAXIMUM TOTAL COMPARTMENT LOAD: 300 LB (136 KG) 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 in Forward Flight . . . . . . . . . . . 3-5 Loss of Tail Rotor Thrust in Hover . . . . . . . . . . . . . . . . . 3-5 Headset Audio Failure . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5 Engine Fire During Start or Shutdown . . . . . . . . . . . . . . 3-6 Engine Fire in 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 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 13 MAR 2020 3-i INTENTIONALLY BLANK 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 airspeed. 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: 19 OCT 2016 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 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES EMERGENCY WATER LANDING - POWER OFF 1. Follow same procedures as for power failure over land until contacting water. If time permits, unlatch doors prior to water contact. 2. Apply lateral cyclic when aircraft contacts water to stop rotors. 3. Release seat belt and quickly clear aircraft when rotors stop. EMERGENCY WATER LANDING - POWER ON 1. Descend to hover above water. 2. Unlatch doors. 3. Passengers exit aircraft. 4. Fly to safe distance from passengers to avoid possible injury by blades. 5. Switch battery and generator OFF. 6. Close throttle. 7. Keep aircraft level and apply full collective as aircraft contacts water. 8. Apply lateral cyclic to stop rotors. 9. Release seat belt and quickly clear aircraft when rotors stop. FAA APPROVED: 25 OCT 2010 3-4 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. HEADSET AUDIO FAILURE If headset audio fails, land as soon as practical. CAUTION For aircraft which provide low RPM horn through the audio system, pilot will not hear horn with a failed headset. ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 13 MAR 2020 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