R66 PILOT'S OPERATING HANDBOOK AND FAA APPROVED ROTORCRAFT FLIGHT MANUAL

procedures, and operational handling characteristics of the helicopter before flight. This handbook has been divided into ten numbered sections. Limitations and emergency procedures have been placed ahead of normal procedures, performance, and other sections to provide easier access to that information. Provisions for expansion of the handbook have been made by deliberate omission of certain paragraph numbers, figure numbers, item numbers, and pages noted as being intentionally blank. 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 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: 13 MAR 2020 3-9 AMBER CAUTION INDICATORS (cont’d) GEN Indicates generator failure. Turn off non- essential 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 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 Indicates rotor speed below 95% RPM. To restore RPM, immediately lower collective, verify throttle full open and, in forward flight, apply aft cyclic. COWL DOOR Indicates baggage compartment door, fuel filler cowl door, or an engine cowl 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. HYD (if installed) Indicates hydraulic system is switched off. FAA APPROVED: 21 JUN 2021 3-10 ROBINSON MODEL R66 SECTION 3 EMERGENCY PROCEDURES AUDIO ALERTS R66 helicopters provide the following audio alerts: LOW RPM HORN Horn is provided by speakers in the side of the instrument console on earlier aircraft or through the audio system on later aircraft. The horn activates simultaneously with LOW RPM on the annunciator panel and indicates rotor speed below 95% RPM. To restore RPM, lower collective, verify throttle full open, and, in forward flight, apply aft cyclic. Horn is disabled when collective is full down. HIGH RPM WARBLE On later aircraft, a warble (high/low tone) in the audio system indicates rotor speed is approaching the 106% RPM limit. Raise collective as required to control RPM. HIGH TORQUE/MGT BEEP On later aircraft, a beeping tone in the audio system indicates either engine torque above 100% or MGT above 782°C (above 5-minute limits). Lower collective to reduce power. A beeping tone during start indicates MGT above 860°C. To avoid exceeding 927°C start limit, immediately pull fuel cutoff OFF, wait ten seconds, then turn igniter switch OFF to stop starter. 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 Doors-Off Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-10 Practice Autorotation - Power Recovery . . . . . . . . . . . . 4-11 Practice Autorotation - With Ground Contact . . . . . . . . . 4-12 Hydraulics-Off Training . . . . . . . . . . . . . . . . . . . . . . . . . 4-12 Descent, Approach, and Landing . . . . . . . . . . . . . . . . . . 4-13 Shutdown Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14 N1 Deceleration Check . . . . . . . . . . . . . . . . . . . . . . . . . . 4-15 Avoiding Hot Starts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-16 Noise Abatement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-18 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 JUN 2021 4-i INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 18 APR 2018 4-1 SECTION 4 NORMAL PROCEDURES RECOMMENDED AIRSPEEDS Takeoff and Climb 60 KIAS Maximum Range 100 KIAS* Maximum Cruise 110 KIAS* (Do not exceed except in smooth air, and then only with caution) Significant turbulence 60 to 70 KIAS Landing Approach 60 KIAS Autorotation 60 to 70 KIAS * Certain conditions may require lower airspeed. See Vne placard in Section 2. DAILY OR PREFLIGHT CHECKS Remove ground handling wheels and all covers and 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 rivets and seams where parts are joined together. Fretting of aluminum parts produces a fine black powder while fretting of steel parts produces a reddish-brown or black residue. Verify 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 no fuel odor in baggage compartment 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: 29 AUG 2017 4-2 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 23 DEC 2022 4-3 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 NOTE If shut down for more than 15 minutes, engine oil level may read low. Motor engine with starter for 30 seconds and re-check before adding oil. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES DAILY OR PREFLIGHT CHECKS (cont’d) 7. Nose Verify pitot tube clear Verify windshield clean and undamaged Check yaw string 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. FAA APPROVED: 23 DEC 2022 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, begin timing N1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15%, increasing MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Below 150°C Fuel cutoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Push ON Successful ignition . . . . . . . . . . . . . . . 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; 16% N1 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% N1 . . . . . . . . . . . . . . . . . . . . . . . . . Main rotor rotating Oil pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . Increasing N1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 Audio alerts (if equipped) . . . . . . . . . . . . . . . . . . . . . . . Test Engine anti-ice check . . . . . . . . . . . . . . . . Annunciator light Doors (if installed) . . . . . . . . . . . . . . . . . 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 N1 deceleration check . . . . . . . . . . . . . . . . . . . . . as desired N2/R . . . . . . . . . . . . . . . . Stable at 100% (beep as required) Annunciator lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Engine gages . . . . . . . . . . . . . . . . . Normal operating range ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 13 MAR 2020 4-7 STARTING ENGINE AND RUN-UP (cont’d) CAUTION For aircraft which provide low RPM horn through the audio system, a headset for each pilot is required to hear the horn. 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 N2 yellow arc. CAUTION When opening throttle, avoid exceeding 50% torque. On slippery surfaces, be prepared to counter nose-right rotation with left pedal. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 13 MAR 2020 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. 4. Beep RPM as required to 100%. 5. Check gages in green and note hover torque. 6. 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 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. 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: 21 JUN 2021 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 airspeed limits. Maximum recommended cruise speed is 110 KIAS. 3. Verify gages in green, no cautions or warnings. 4. Engine anti-ice as required. CAUTION Do not exceed 110 KIAS except in smooth air and then only with caution. In turbulence, use lower airspeed. If turbulence is significant or becomes uncomfortable for the pilot, use 60 to 70 KIAS. 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. FAA APPROVED: 21 JUN 2021 4-10 ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 23 DEC 2022 4-11 PRACTICE AUTOROTATION - POWER RECOVERY CAUTION Verify a recent N1 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 within limits. 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 N2 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: 19 OCT 2016 4-13 DESCENT, APPROACH, AND LANDING 1. Reduce power with collective as desired. Observe airspeed limits. Maximum recommended airspeed is 110 KIAS except in smooth air. CAUTION Do not initiate a descent with forward cyclic. This can produce a low-G condition. Always initiate a descent by lowering collective. 2. Make final approach into wind at lowest practical rate of descent with initial airspeed of 60 knots. 3. Reduce airspeed and altitude smoothly to hover. (Be sure rate of descent is less than 300 feet per minute before airspeed is reduced below 30 KIAS.) 4. From hover, lower collective gradually until ground contact. 5. After initial ground contact, lower collective to full down position. CAUTION When landing on a slope, return cyclic control to neutral before 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: 23 DEC 2022 4-14 SHUTDOWN PROCEDURE Collective down . . . . . . . . . . . . . . . . . . . . . . . . Friction ON Throttle closed . . . . . . . . . . . . . . . . . N1 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 N2/R needles split Wait one minute . . . . . . . . . . . . . . . . . . . Apply rotor brake Avionics, generator, battery, igniter switches . . . . . . . . OFF CAUTION Applying rotor brake less than one minute after fuel cutoff may cause heat damage to brake shoes and gearbox oil seal. NOTE After engine shutdown, pilot should uncover one ear and listen for unusual noise which may indicate impending failure of a bearing or other component. CAUTION Do not slow rotor by raising collective during shutdown. Blades may flap and strike tailcone. NOTE HYD switch should be left ON for 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: 19 OCT 2016 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 during the preflight run-up if autorotations are planned during the flight and again during shutdown. A failed check is an indication that the engine may flame out 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: 21 JUN 2021 4-16 AVOIDING HOT STARTS Exceeding temperature limits during a turbine start (a “hot start”) can cause severe engine damage requiring expensive repairs. 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 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. 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. BEFORE INITIATING A START: • Verify battery voltage is normal. If battery voltage is low (less than approximately 24.5 volts for lead-acid or 26.0 volts for lithium-ion), use ground power and/or replace battery. • Verify fuel cutoff is pulled completely off. • Verify twist grip is completely closed (rotated toward pilot). ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 JUN 2021 4-17 AVOIDING HOT STARTS (cont’d) DURING A START: • DO NOT push fuel cutoff on until N1 is smoothly rising through 16%. If starter is sluggish or will not achieve 16%, do not introduce fuel. Switch starter off using igniter (key) switch. • If engine is warm from a previous flight, DO NOT push fuel cutoff on until MGT is below 150°C. As starter accelerates engine to 16% N1, MGT typically falls below 150°C. However, extra time may be required to allow residual temperature to decrease. • After pushing 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. ROBINSON MODEL R66 SECTION 4 NORMAL PROCEDURES FAA APPROVED: 21 JUN 2021 4-18 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. ROBINSON MODEL R66 SECTION 5 PERFORMANCE CONTENTS SECTION 5 PERFORMANCE Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Use of Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Airspeed Calibration Curve . . . . . . . . . . . . . . . . . . . 5-4 Density Altitude Chart . . . . . . . . . . . . . . . . . . . . . . 5-5 Power Assurance Chart . . . . . . . . . . . . . . . . . . . . . 5-6 IGE Hover Ceiling Vs. Gross Weight . . . . . . . . . . . . . 5-7 OGE Hover Ceiling Vs. Gross Weight . . . . . . . . . . . . 5-8 Climb Performance, 2700 lb Gross Weight . . . . . . . . . 5-9 Climb Performance, 2200 lb Gross Weight ......... 5-10 Height-Velocity Diagram ...................... 5-11 Noise Characteristics ....................... 5-12 FAA APPROVED: 25 OCT 2010 5-i INTENTIONALLY BLANK FAA APPROVED: 21 JUN 2021 5-1 SECTION 5 PERFORMANCE GENERAL Hover controllability has been substantiated in 17 knot wind from any direction up to 11,000 feet (3350 meters) density altitude. Refer to hover performance charts for allowable gross weight. CAUTION Performance data presented in this section was obtained under ideal conditions. Performance under other conditions may be substantially less. Indicated airspeed (KIAS) shown on charts assumes zero instrument error. USE OF CHARTS DENSITY ALTITUDE CHART Aerodynamic performance of a helicopter rotor system is greatly affected by air density, usually stated as density altitude. Density altitude can be read from the chart using known pressure altitude and temperature. For example, the helicopter altitude limit is 14,000 feet density altitude and maximum temperature limit is ISA+35°C. The chart shows that 14,000 feet density altitude is over 16,000 feet pressure altitude at –40°C but only 10,200 feet pressure altitude at maximum ambient temperature of 30°C. Vne tables in Section 2 indicate “no flight” for altitude/ temperature combinations which exceed 14,000 feet density altitude or ISA+35°C limits. Note that the actual maximum allowable temperature at a given altitude may be greater than what is given in the tables. For example, the Density Altitude Chart shows maximum allowable temperature at 2,000 feet pressure altitude is 46°C. Vne at this condition may be estimated by extrapolation from the table. ROBINSON MODEL R66 SECTION 5 PERFORMANCE ROBINSON MODEL R66 SECTION 5 PERFORMANCE FAA APPROVED: 21 JUN 2021 5-2 USE OF CHARTS (cont’d) POWER ASSURANCE CHART The power assurance chart shows maximum allowable MGT at a specified torque. If observed MGT is greater than indicated by the chart, the engine may not be producing 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. 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. HOVER PERFORMANCE In-ground-effect (IGE) and out-of-ground-effect (OGE) hover performance is given in the Hover Ceiling vs. Gross Weight charts on pages 5-7 and 5-8, respectively. Note that hover performance is limited by the MGT five- minute limit, not by torque or tail rotor authority. Hover performance is substantiated up to 11,000 feet (3350 meters) density altitude; however, data is presented beyond 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 2700 lb (1225 kg) up to 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): ROBINSON MODEL R66 SECTION 5 PERFORMANCE USE OF CHARTS (cont’d) HOVER PERFORMANCE (cont’d) Pressure altitude: 9000 ft 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 9000 ft pressure altitude and 32°C OAT are therefore used with the charts, giving a maximum weight of 2580 lb (1170 kg) for IGE hover and 2320 lb (1050 kg) for OGE hover. If wind is present, subtract an additional 100 lb (45 kg) IGE and 50 lb (23 kg) OGE per note on chart. This provides a power margin for transient control inputs up to 17 knot wind regardless of azimuth. CLIMB PERFORMANCE Climb performance charts are given for 2700 lb (1225 kg) and 2200 lb (998 kg) gross weight at 60 KIAS climb speed 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 only a small effect on climb rate. Note that predicted climb rate is approximate; variations in aircraft and operating conditions may significantly affect performance. HIGH-VELOCITY DIAGRAM The height-velocity diagram is given for maximum gross weight at sea level and at 7800 feet (2380 meters) density altitude. An appropriate line for altitudes between sea level and 7800 feet may be estimated by interpolation. For example, a line with a hover point at 600 feet AGL may be used for 3900 feet density altitude. FAA APPROVED: 21 JUN 2021 5-3 ROBINSON MODEL R66 SECTION 5 PERFORMANCE NOTE: INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR 140 UJ <C 120 u ::.:: C 100 w w Q. UJ a: 80 <C C w I- 60 <C a: co ::::i <C 40 u 20 0 0 20 40 60 80 100 120 140 INDICATED AIRSPEED - KIAS AIRSPEED CALIBRATION CURVE FAA APPROVED: 25 OCT 2010 5-4 I- w w LL w' 0 ::, I- ~ -' <! >-I- en z w 0 ROBINSON MODEL R66 18000 16000 14000 12000 10000 8000 6000 4000 2000 SECTION 5 PERFORMANCE - 2 000 '--""-..l.---""--'----'"---.1...--"""---'---"----J----'"----'-.......--'----''----'--.......---'---' - 40 - 30 - 20 - 10 0 10 20 30 I I I I I I I I I I -40 -20 TEMPERATURE, DEGREES C I I I I I I I I I I I I I I I I I I 0 20 40 60 80 TEMPERATURE, DEGREES F DENSITY ALTITUDE CHART 40 50 I I I, I i I I I 100 120 FAA APPROVED: 25 OCT 2010 5-5 ROBINSON MODEL R66 UJ ....J a.. ~ <( X UJ SECTION 5 PERFORMANCE 0 -~~-~-~-~~-~-~-~~-~-~~ o 1---,1-t--+-+--+---+-+-t-<1-t-t--t--+---+--t-t-<l-t-+--+--+--+-+-t-t Cl) I, ' ' ' "- "- ~ I"-, "- I',.. ', I',.. LO 1---,1-t--+-+--+---+-+-;-.,.,-+---+-+-"'~,---- +-"'<-, -+---+-.......t-,-+--+-'..., -+--t POWER ASSURANCE CHART FAA APPROVED: 25 OCT 2010 5-6 ROBINSON MODEL R66 SECTION 5 PERFORMANCE FAA APPROVED: 17 MAR 2021 5-7 I- LL 0 0 0 >< a. I w 0 ::, I- i= -' <( w 0: ::, en enw 0: a.. IN GROUND EFFECT AT 2 FOOT SKID HEIGHT AND ZERO WIND MGT 5-MINUTE LIMIT 13 12 11 10 9 8 7 6 5 4 3 2 2200 ENGINE ANTI-ICE AND CABIN HEAT OFF 50 AMP GENERATOR LOAD GROSS WEIGHT - KG 1050 11 00 1150 1200 1250 4000 3500 3000 2500 '/- <to 2000 1500 • WITH ENGINE ANTI - ICE ON , ADD 10 ° C TO OAT • WITH FULL CABIN HEAT, ADD 20 ° C TO OAT • FOR GENERATOR LOAD OVER 50 AMPS, ADD 1000 1 °C PER 20 AMPS TO OAT • FOR WIND UP TO 17 KNOTS , SUBTRACT 100 LB 145 KG) TO ALLOW FOR POWER TRANSIENTS 2300 2400 2500 2600 2700 2800 GROSS WEIGHT - LB IGE HOVER CEILING VS. GROSS WEIGHT NOTE: Hover performance substantiated up to 11,000 feet (3350 meters) density altitude . Data is presented only to determine performance with engine anti-ice, cabin heat and /or generator loads over 50 amps . en 0: w I- w ~ >< a. I w 0 ::, I- i= -' <( w 0: ::, en enw 0: a.. FAA APPROVED: 17 MAR 2021 5-8 ROBINSON MODEL R66 SECTION 5 PERFORMANCE I- LL 0 0 0 >< a. I LU 0 ::, I- i== -' <( LU a: ::, (/) (/) LU a:[l_ OUT OF GROUND EFFECT , ZERO WIND MGT 5-MINUTE LIMIT ENGINE ANT I-ICE AND CABIN HEAT OFF 50 AMP GENERATOR LOAD GROSS WEIGHT - KG 1000 14 1050 1100 1150 1200 13 12 11 10 9 8 7 6 5 4 3 2 • WITH ENGINE ANTI-ICE ON, ADD 10 ° C TO OAT • WITH FULL CABIN HEAT, ADD 20 ° C TO OAT • FOR GENERATOR LOAD OVER 50 AMPS, ADD 1 °C PER 20 AMPS TO OAT • FOR WIND UP TO 17 KNOTS, SUBTRACT 50 LB 123 KG) TO ALLOW FOR POWER TRANSIENTS 1250 4000 3500 3000 (/) a: LU I- LU ~ 2500 >< a. I LU 0 ::, 1- 2000 i== -' <( LU a: ::, (/) 1500 ~ 1000 500 a:[l_ 1 2200 2300 2400 2500 2600 2700 2800 GROSS WEIGHT - LB OGE HOVER CEILING VS. GROSS WEIGHT * Hover performance substantiated up to 11,000 feet (3350 meters) density altitude. Data beyond ISA+ 35 ° C and above 11 , 000 feet 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 5 PERFORMANCE I- IL 0 0 0 X C. I 'LU Cl ::::, I- i==-1 <( LU cc ::::, (/) (/) LU cc a.. MAXIMUM CONTINUOUS TORQUE OR MAXIMUM CONTINUOUS MGT 60 KIAS CLIMB SPEED 14 13 12 11 10 9 8 7 6 5 4 3 2 1 ENGINE ANTI-ICE AND CABIN HEAT OFF CLIMB RATE, FT/MIN ENGINE ANTI-ICE MAY REDUCE CLIMB RATE UP TO 300 FT/MIN FULL CABIN HEAT MAY REDUCE CLIMB RATE UP TO 600 FT/MIN CLIMB PERFORMANCE, 2700 LB GROSS WEIGHT FAA APPROVED: 25 OCT 2010 5-9 ROBINSON MODEL R66 SECTION 5 PERFORMANCE r-u.. 0 0 0 X Q. :c .w c::::i ::i r- 5<( w a: ::i en enw a: 0.. MAXIMUM CONTINUOUS TORQUE OR MAXIMUM CONTINUOUS MGT 60 KIAS CLIMB SPEED ENGINE ANTI-ICE AND CABIN HEAT OFF 14 13 12 11 10 9 8 7 6 5 4 3 ISA + 35 ° 2 1 0 500 700 900 1100 1300 1500 1700 CLIMB RATE, FT/MIN ENGINE ANTI-ICE MAY REDUCE CLIMB RATE UP TO 400 FT/MIN FULL CABIN HEAT MAY REDUCE CLIMB RATE UP TO 700 FT/MIN CLIMB PERFORMANCE, 2200 LB GROSS WEIGHT FAA APPROVED: 25 OCT 2010 5-10 FAA APPROVED: 26 NOV 2013 5-11 ROBINSON MODEL R66 SECTION 5 PERFORMANCE ROBINSON MODEL R66 SECTION 5 PERFORMANCE FAA APPROVED: 27 SEP 2023 5-12 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: 2700 lb (1225 kg) Configuration Vh KTAS Noise Level (EPNdB) Flyover Takeoff Approach Earlier Version Clean 117 84.5 87.8 87.8 Dirty 108 84.8 87.8 88.6 Later Version Clean 117 84.2 86.2 86.1 Dirty 109 84.6 87.1 89.5 Notes: 1. Configurations are: Earlier version - Horizontal Stabilizer is mounted adjacent to tail gear box. Later version - Horizontal Stabilizer is mounted under tailcone forward of tailrotor. 2. The dirty configuration has air conditioning and four doors with bubble windows installed, and landing gear strut fairings removed. These noise levels meet the requirements for a Stage 3 helicopter as defined in 14 CFR Part 36. NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be accept- able or unacceptable for operation at, into, or out of any airport. ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1 Weight and Balance Record Loading Instructions ISSUED: 25 OCT 2010 6-2 6-4 6-i INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE GENERAL SECTION 6 WEIGHT AND BALANCE The helicopter must be flown only within weight and balance limits specified in Section 2. Loadings outside these limits can result in insufficient control travel for safe operation. The center of gravity may be adjusted by adding removable ballast (any appropriate item of mass) to the baggage compartment and any under seat stowage area. Recal- culate weight and balance after adding ballast, and verify ballast meets baggage compartment/stowage area limits given in Section 2. Loaded helicopter weight and balance can be determined using the method given under LOADING INSTRUCTIONS. In accordance with FAA procedures, the detail weight and balance data of this section are not subject to FAA approval. The loading instructions of this section, however, have been approved by the FAA as satisfying all requirements for instructions on loading of the rotorcraft within approved limits of weight and center of gravity and on maintaining the loading within such limits. CAUTION Fuel burn causes CG to move forward during flight. Always determine safe loading with empty fuel as well as with takeoff fuel. Payload may be limited by forward CG as fuel is burned. ISSUED: 25 OCT 2010 6-1 ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD The following form should be used to maintain a continuous record of your helicopter's weight and balance. Each time an item of equipment is removed or installed, an entry must be made and the new empty CG determined. The original factory weight and configuration is supplied with each helicopter on the Weight and Balance Summary/Equipment List (RF 134) at the end of this section. The RF 134 Weight and Balance Summary provides the first entry in the Weight and Balance Record. NOTE Calculated CG of empty weight plus 160 lb pilot must be STA 102.5 or forward. Following modification, adjustment to fixed nose ballast may be required. See R66 Maintenance Manual. ISSUED: 25 OCT 2010 6-2 ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE ISSUED: 25 OCT 2010 6-3 WEIGHT AND BALANCE RECORD (cont’d) WEIGHT AND BALANCE RECORD (Continuous History of Changes in Structure or Equipment Affecting Weight and Balance) HELICOPTER MODEL R66 SERIAL NUMBER: DATE DESCRIPTION OF ARTICLE OR MODIFICATION WEIGHT CHANGE RUNNING BASIC EMPTY WEIGHT ADDED (+) REMOVED (—) WEIGHT (lb) LONGITUDINAL LATERAL (+ = RIGHT SIDE) WEIGHT (lb) LONGITUDINAL LATERAL Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) Arm (in.) Moment (in.-lb) HELICOPTER AS WEIGHED ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE REVISED: 23 DEC 2022 6-4 LOADING INSTRUCTIONS The following table may be used when calculating loaded helicopter weight and CG position. COMMON ITEM WEIGHT & CG Item Weight (lb) Longitudinal arm (in.) Lateral arm (in.) ( + = right side) Pilot (right forward seat) 49.0* 12.2 Left forward passenger 49.0* −12.2 Aft outboard passengers 80.0 ±16.0 Aft center passenger 78.0 0.0 Baggage under forward seats 42.0 ±12.2 Baggage under aft seats 82.0 ±15.0 Baggage in baggage compartment 107.0 0.0 Fuel 102.5 −3.0 Forward doors 7.5 each 49.5 ±26.8 Aft doors 7.0 each 75.2 ±27.2 Removable controls (cyclic, collective, pedals) 2.0 31.0 −13.0 Items on accessory mount bars 23.0 ±14.0 * If additional backrest cushion is used, subtract thickness of compressed cushion. ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE REVISED: 23 DEC 2022 6-5 LOADING INSTRUCTIONS (cont’d) The following sample calculation demonstrates how to determine loaded helicopter weight and center of gravity. A worksheet is provided on the page following the sample calculation for a weight and balance calculation for your helicopter. Calculated weight and balance must be compared with the CG limits given in Section 2 to determine safe loading. Both takeoff and empty fuel conditions must be within limits. Lateral CG usually falls well within limits for conventional loadings. If an unusual lateral installation or loading occurs, lateral CG should be checked against the CG limits given in Section 2. The lateral reference datum is the aircraft centerline with items to the right positive and items to the left negative. ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE REVISED: 23 DEC 2022 6-6 LOADING INSTRUCTIONS (cont’d) SAMPLE LOADING CALCULATION Item Weight (lb) Location Moment Long. Arm (in.) Lat. Arm (in.) += Right Side Long. (in.-lb) Lat. (in.-lb) Basic empty weight 1290 140610 431 Remove forward right door −7.5 49.5 26.8 −371 −201 Remove forward left door 49.5 −26.8 Remove aft right door 75.2 27.2 Remove aft left door 75.2 −27.2 Remove left seat controls 31.0 −13.0 Pilot (forward right seat) 170 49.0 12.2 8330 2074 Left forward passenger 170 49.0 −12.2 8330 −2074 Aft right passenger 170 80.0 16.0 13600 2720 Aft center passenger 130 78.0 0.0 10140 0 Aft left passenger 170 80.0 −16.0 13600 −2720 Baggage under forward right seat 10 42.0 12.2 420 122 Baggage under forward left seat 10 42.0 −12.2 420 −122 Baggage under aft right seat 10 82.0 15.0 820 150 Baggage under aft left seat 10 82.0 −15.0 820 −150 Baggage in main baggage comp. 50 107.0 0.0 5350 0 Items on accessory mount bars 5 23.0 14.0 115 70 Zero usable fuel weight and CG 2187.5 92.4 0.1 202184 300 Usable main fuel at 6.7 lb/gal. 493.1 102.5 −3.0 50543 −1479 Takeoff Gross Weight and CG 2680.6 94.3 −0.4 252612 −1179 Note: CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE REVISED: 23 DEC 2022 6-7 LOADING INSTRUCTIONS (cont’d) LOADING CALCULATION WORKSHEET Item Weight (lb) Location Moment Long. Arm (in.) Lat. Arm (in.) += Right Side Long. (in.-lb) Lat. (in.-lb) Basic empty weight Remove forward right door 49.5 26.8 Remove forward left door 49.5 −26.8 Remove aft right door 75.2 27.2 Remove aft left door 75.2 −27.2 Remove left seat controls 31.0 −13.0 Pilot (forward right seat) 49.0 12.2 Left forward passenger 49.0 −12.2 Aft right passenger 80.0 16.0 Aft center passenger 78.0 0.0 Aft left passenger 80.0 −16.0 Baggage under forward right seat 42.0 12.2 Baggage under forward left seat 42.0 −12.2 Baggage under aft right seat 82.0 15.0 Baggage under aft left seat 82.0 −15.0 Baggage in main baggage comp. 107.0 0.0 Items on accessory mount bars 23.0 Zero usable fuel weight and CG Usable fuel quantity at 6.7 lb/gal. 102.5 −3.0 Takeoff Gross Weight and CG Note: CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. THIS PAGE INTENTIONALLY BLANK ISSUED: 25 OCT 2010 6-8 ROBINSON MODEL R66 SECTION 6 WEIGHT AND BALANCE ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 JUN 2021 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 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-12 Lighting System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-16 External Power Receptacle . . . . . . . . . . . . . . . . . . . . . . 7-17 Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-17 Annunciator Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-20 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-21 Audio System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22 Optional Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Dual Tachometer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Pitot-Static System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-24 Engine Monitoring Unit . . . . . . . . . . . . . . . . . . . . . . . . . 7-24 Cabin Heating and Ventilation . . . . . . . . . . . . . . . . . . . . 7-25 Seats, Belts, and Baggage . . . . . . . . . . . . . . . . . . . . . . . 7-26 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-27 Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-28 ADS-B Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-29 Emergency Locator Transmitter (Optional) . . . . . . . . . . . 7-30 Accessory Mounts (Optional) . . . . . . . . . . . . . . . . . . . . 7-31 Cockpit Camera (Optional) . . . . . . . . . . . . . . . . . . . 7-32 Cyclic Guard (Optional) . . . . . . . . . . . . . . . . . . . 7-33 INTENTIONALLY BLANK ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 21 JUN 2021 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. Optional doors with large bubble windows intended for use during external load operations have specific operating limitations and procedures. See Cargo Hook Equipment Supplement. 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. /SKIN 1~1111111111111111111111111[DSPARHONEYCOMB · .... · 7 SKIN-TO-SPAR BOND LINE MAIN ROTOR BLADE CONSTRUCTION ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION ISSUED: 25 OCT 2010 7-3 DRIVE SYSTEM The engine is mounted in a 37° nose-up attitude. A sprag- type overrunning clutch mates directly to the splined engine power take-off (PTO) shaft. The clutch is connected to a shaft with flexible couplings at both ends to transmit power to the main gearbox. A ring and pinion spiral bevel gearset at the main gearbox input reduces speed to tail rotor driveline RPM. A second ring and pinion stage reduces speed from tail rotor driveline RPM to main rotor RPM. The tail rotor drive line consists of an intermediate shaft running aft from the main gearbox and a long tail rotor driveshaft which runs the length of the tailcone. Flexible couplings are located at both ends of the intermediate shaft. The long tail rotor driveshaft has a support bearing at its front end and a damper bearing approximately one- third of the way aft on the shaft. The cooling fan is mounted to the intermediate shaft. The tail gearbox contains a single 90° splash-lubricated spiral-bevel gearset which increases speed to tail rotor RPM. The main gearbox is pressure lubricated. The oil is pumped through an airframe-mounted filter and cooled by an oil cooler which receives its airflow from the cooling fan. The main gearbox also drives the flight control hydraulic pump. ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 29 AUG 2017 7-4 POWERPLANT INSTALLATION One Rolls-Royce model 250-C300/A1 (commercial desig- nation RR300) free-turbine turboshaft engine powers the helicopter. The engine is equipped with an ignition excit- er, igniter, starter-generator, two tachometer senders, and additional powerplant instrument senders. See sections 1 and 2 for power plant specifications and limitations. A direct-drive, squirrel-cage style cooling fan is mounted to the intermediate shaft and supplies cooling air to the engine and gearbox oil coolers. Induction air enters through multiple openings in the upper fuselage cowlings and flows into a plenum forward of the firewall. The plenum contains a radial-flow air filter at the engine compressor inlet. The standard filter element is foam. A high-efficiency filter element with pleated media is optional. The high-efficiency filter includes a sight gage inside the upper left cowl door which provides an indication of filter dirt load. NOTE The high-efficiency filter is recommended for operating in dusty conditions. The standard filter may not filter fine sand or dust, resulting in reduced engine life. If the air filter becomes blocked, spring-loaded doors at the front of the filter housing open, allowing unfiltered air to the engine. The AIR FILTER annunciator illuminates when filter bypass is occurring. NOTE Periodically performing power assurance checks may provide indication of engine deterioration or air filter blockage. Main- tenance actions such as air filter cleaning and compressor wash should be performed if aircraft fails power assurance check (see Section 5 for power assurance check and Maintenance Manual for maintenance procedures). ROBINSON MODEL R66 SECTION 7 SYSTEMS DESCRIPTION REVISED: 6 JUL 2018 7-5 POWERPLANT INSTALLATION (cont’d) A temperature switch is mounted to the firewall above the engine to detect a fire in the engine compartment. Abnormally high temperature causes the ENGINE FIRE annunciator to illuminate. 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. Left-side pedals are not adjustable. However, optional pedals designed for shorter pilots (Robinson part nos. F755-9 and -10) may be installed in place of the standard pedals. 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 HYDRAULIC SYSTEM Hydraulically-boosted main rotor flight controls eliminate cyclic and collective feedback forces. The hydraulic system consists of a pump, three servos, a reservoir, and interconnecting lines. Normal operating pressure is 450 to 500 psi. The pump is mounted on and driven by the main gearbox. A servo is connected to each of the three push- pull tubes that support the main rotor swashplate. The reservoir is mounted to the aft end of the main gearbox and includes a filter, pressure relief valve, and pilot-controlled pressure shut-off valve. A sight glass for pre-flight fluid level checks is incorporated in the reservoir and accessible via a left side cowl door. A vented filler cap is located on top of the reservoir. The pressure shut-off valve is solenoid-actuated and controlled by the hydraulic switch on the pilot's cyclic grip. The switch should be left ON during helicopter shutdown and start up except during the hydraulic system check. NOTE Electrical power is required to switch hydraulics OFF. Pulling HYO circuit breaker will NOT turn off hydraulics but will disable hydraulic switch. Without hydraulic pressure, a large pilot input force is required to increase collective. Collective inputs also cause longitudinal cyclic forces which makes it difficult to maintain a steady hover. The servos have an irreversible feature to prevent rotor feedback forces from moving the controls. This allows the pilot to relax pressure on the controls in steady cruise flight. However, any cyclic input will cause the collective to lower and therefore the collective will have to be increased periodically. ISSUED: 25 OCT 2010 7-7 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