PILOT'S OPERATING HANDBOOK AND FAA APPROVED ROTORCRAFT FLIGHT MANUAL

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. REVISED: 26 JUN 2012 1-1 ROBINSON R22 SERIES 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. REVISED: 26 JUN 2012 1-2 ROBINSON R22 SERIES SECTION 1 GENERAL REVISED: 22 FEB 2024 1-3 R22 EXTERNAL DIMENSIONS (LATER AIRCRAFT SHOWN) EXTERNAL DIMENSIONS ROBINSON R22 SERIES SECTION 1 GENERAL REVISED: 11 MAY 2020 1-4 DESCRIPTIVE DATA MAIN ROTOR Articulation Free to teeter and cone, rigid inplane Number of Blades 2 Diameter 25 feet 2 inches Blade Chord 7.2 inches inboard, 7.7 inches outboard Blade Twist -8 degrees Tip Speed at 104% RPM 698 feet per second TAIL ROTOR Articulation Free to teeter, rigid inplane Number of Blades 2 Diameter 42 inches Blade Chord 4 inches (constant) Blade Twist 0 degrees Precone Angle 1 degree 11 minutes Tip Speed at 104% RPM 622 feet per second DRIVE SYSTEM Engine to Upper Sheave: Two double Vee-belts with .8536:1 speed reducing ratio Upper Sheave to Drive Line: Sprag-type overrunning clutch Drive Line to Main Rotor: Spiral-bevel gears with 11:47 speed reducing ratio Drive Line to Tail Rotor: Spiral-bevel gears with 3:2 speed increasing ratio ROBINSON MODEL R22 SECTION 1 GENERAL DESCRIPTIVE DATA (cont'd) POWERPLANT Model: Lycoming 0-320 or 0-360 Type: Four cylinder, horizontally opposed, direct drive air cooled, carbureted, normally aspirated Displacement: 319.8 (0-320) or 361.0 (0-360) cubic inches Normal rating: 0-320-A2B or A2C 150 BHP @ 2700 RPM (Standard R22) 0-320-B2C 160 BHP@ 2700 RPM (R22 HP, Alpha, and Beta) 0-360-J2A 145 BHP (derated) @ 2700 RPM (R22 Beta II) Maximum continuous rating in R22: 124 BHP at 2652 RPM ( 1 04 % on tachometer) 5 minute takeoff rating for Beta and Beta II only: 131 BHP at 2652 RPM Cooling system: Direct drive squirrel-cage blower FUEL Approved fuel grades and capacity: See Section 2. OIL Approved oil grades and capacity: See Section 8. REVISED: 23 DEC 2009 1-5 ROBINSON MODEL R22 SECTION 1 GENERAL PERFORMANCE DEFINITIONS KIAS KCAS KTAS vne Vv MSL Altitude Pressure Altitude Density Altitude ISA BHP MAP RPM MCP TOP Critical Altitude TOGW 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 page 5-2 for position error correction.) Knots True Airspeed is airspeed relative to undis- turbed air. It is KCAS corrected for pressure altitude and temperature. Never-Exceed Airspeed. Speed for best rate of climb. Altitude above sea level, in feet, indicated by the al- timeter (corrected for position and instrument error) when the barometric subscale is set to the atmospheric pressure existing at sea level. Altitude, in feet, indicted by the altimeter (corrected for position and instrument error) when the barom- etric subscale is set to 29.92 inches of mercury (1013.2 mb). Altitude, in feet, 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 1 000 feet of altitude. Brake Horsepower is actual power output of the engine. Manifold Pressure is the absolute pressure, in inches of mercury, in the engine intake manifold. Revolutions Per Minute or speed of engine or main rotor. (Shown by tachometer as percentage of 2550 engine RPM or 510 main rotor RPM). Maximum Continuous Power. Takeoff Power (usually for a maximum of 5 minutes). Altitude at which full throttle produces maximum al- lowable power (MCP or TOP). Takeoff Gross Weight. REVISED: 23 DEC 2009 1-6 REVISED: 5 MAR 2015 1-7 ROBINSON R22 SERIES SECTION 1 GENERAL PERFORMANCE DEFINITIONS (cont’d) OAT Outside Air Temperature CAT Carburetor Air Temperature CHT Cylinder Head Temperature GPH Gallons Per Hour AGL Above Ground Level IGE In Ground Effect OGE Out of Ground Effect ALT Alternator WEIGHT AND BALANCE DEFINITIONS Reference Datum A vertical plane from which horizontal distances are measured for balance purposes. The longitudinal reference datum is 100 inches forward of the main rotor shaft centerline for the R22. Station Fore-and-aft location along the helicopter fuselage given in terms of distance in inches from the longitudinal reference datum. Arm Horizontal distance from a reference datum to the center of gravity (CG) of an item. Moment The weight of an item multiplied by its arm. Center of Gravity (CG) Location along the fuselage (usually expressed in inches from the reference datum) at which the helicopter would balance. CG is calculated by dividing the total helicopter moment by total helicopter weight. CG Limits Extreme CG locations within which the heli- copter must be operated at a given weight. Usable Fuel Fuel available for flight planning. Unusable Fuel Fuel remaining in the tank that cannot reliably provide uninterrupted fuel flow in the critical flight attitude. Standard Empty Weight Weight of standard helicopter including unusable fuel, full operating fluids, and full engine oil. Basic Empty Weight Standard empty weight plus weight of installed optional equipment. Payload Weight of occupants, cargo, and baggage. Useful Load Difference between maximum gross weight and basic empty weight. REVISED: 5 MAR 2015 1-8 ROBINSON R22 SERIES SECTION 1 GENERAL CONVERSION TABLES METRIC TO ENGLISH Multiply By To Obtain centimeters (cm) 0.3937 inches (in) kilograms (kg) 2.2046 pounds (lb) kilometers (km) 0.5400 nautical miles (nm) kilometers (km) 0.6214 statute miles (mi) liters (I) 0.2642 gallons, U.S. (gal) liters (I) 1.0567 quarts (qt) meters (m) 3.2808 feet (ft) millibars (mb) 0.0295 inches mercury (in. Hg) ENGLISH TO METRIC Multiply By To Obtain feet (ft) 0.3048 meters (m) gallons, U.S. (gal) 3.7854 liters (I) inches (in) 2.5400 centimeters (cm) inches (in) 25.4000 millimeters (mm) inches mercury (in. Hg) 33.8638 millibars (mb) nautical miles (nm) 1.8520 kilometers (km) pounds (lb) 0.4536 kilograms (kg) quarts (qt) 0.9464 liters (I) statute miles (mi) 1.6093 kilometers (km) 1 nautical mile = 1.1508 statute miles 1 statute mile = 0.8690 nautical mile TEMPERATURE °F = 9/5 (°C) + 32 °C = 5/9 (°F – 32) ROBINSON MODEL R22 General SECTION 2 LIMITATIONS CONTENTS SECTION 2 LIMITATIONS Page 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 . . . . . . . . . . . . . . . . 2-6 Kinds of Operation Limitations . . . . . . . . . . . . . . . . . 2-7 Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . 2- 7 Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . 2-8 Placards ............................... 2-10 Information per FAA AD 95-26-04 . . . . . . . . . . . . . 2-15 FAA APPROVED: 23 DEC 2009 2-i INTENTIONALLY BLANK ROBINSON R22 SERIES SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS GENERAL This section includes operating limitations, instrument markings, and basic placards required for safe operation of the helicopter, its engine, and other standard systems. The helicoper is approved as a normal category rotorcraft under FAA Type Certificate No. H10WE as Models R22, R22 Alpha, R22 Beta, and R22 Mariner. COLOR CODE FOR INSTRUMENT MARKINGS Red Operating limit. Edge of red line indicates limit. Pointer should not enter red during normal operation. Yellow Precautionary or special operating procedure range. Green Normal operating range. AIRSPEED LIMITS NEVER-EXCEED AIRSPEED (VNE) Up to 3000 feet density altitude: 102 KIAS Above 3000 feet density altitude, see placards on page 2-11. FAA APPROVED: 26 JUN 2012 2-1 ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 17 NOV 2021 2-2 ROTOR SPEED LIMITS Power On Maximum Minimum* 104% (530 RPM) 101% (515 RPM)** Power Off Maximum Minimum 110% (561 RPM) 90% (459 RPM) *Transient operation at lower RPM permitted for emergency procedures training. **97% (495 RPM) permitted on R22s with O-320 engine and tachometer with 97% to 104% green arc installed. POWERPLANT LIMITATIONS ENGINE One Lycoming Model O-320-A2B, -A2C, -B2C, or O-360-J2A. OPERATING LIMITS Engine Speed Maximum continuous 104% (2652 RPM) Maximum transient*** 106% (2700 RPM) Cylinder Head Max Temperature 500°F (260°C) Oil Maximum Temperature 245°F (118°C) Oil Pressure Minimum during idle 25 psi Minimum during flight 55 psi Maximum during flight 95 psi Maximum during start & warm up 115 psi Oil Quantitiy, minimum for takeoff 4 qt (3.8 liters) Manifold Pressure: See placards on pages 2-10 and 2-11 for MAP schedules. ***Intentional operation above maximum continuous speed prohibited. FAA APPROVED: 5 MAR 2015 2-3 ROBINSON R22 SERIES SECTION 2 LIMITATIONS WEIGHT LIMITS Maximum gross weight – Standard & HP 1300 lb (590 kg) Maximum gross weight – Alpha, Beta, and Beta II 1370 lb (622 kg) Minimum gross weight 920 lb (417 kg) Maximum per seat including baggage compartment 240 lb (109 kg) Maximum in either baggage compartment 50 lb (23 kg) CENTER OF GRAVITY LIMITS See figures on pages 2-4 and 2-5. Reference datum is 100 inches forward of main rotor shaft centerline. NOTE With both doors installed, a solo pilot plus baggage weight of 135 lb (61 kg) or greater will ensure CG within limits. For lower 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.) ROB INSON MOD EL R22 SEC T I ON 2 LIMITATIONS FUSELAGE STATION (IN. FROM DATUM) 95 96 97 98 99 1 00 101 1 02 103 1400 Cl ...J 1300 I- :r 1 200 C, iii ==II) 1100 II) 0 a: C, 1 000 900 3 R 2 R a; 1 R C, 0 ~ ...J <a: w I- 1 L <...J 2 L 3 L ... 96 .5 I ... / "',t!1225 ... ~ -1130 - <i - MAIN 2.7 ROTOR ............_ - ...... .... 101.5- / ' 95.5 ......_ l_1.2R - t...., 0.8L - .._ .,,,,,. -0.7L ' ,,,.,..,... " ~ .,,,,,..,,,,,.. 2.2L~__,,., I I 97.5 I I I I I I I I I 242 244 246 2 4 8 250 252 254 256 258 260 FUSELAGE STATI ON (C M FROM DATUM) R22 STANDARD A ND HP CENTER OF GRAVIT Y LIM ITS - - - FAA APPROVED: 1 J UL 2005 650 600 C, ~ 550 I- :r C, iii == 500 II) II) 0 a: 450 C, 400 6 4 :e 0 2 I C, 0 0 ...J <a: - 2 w I- <...J -4 -6 2-4 ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 1 JUL 2005 2-5 R22 ALPHA, BETA, AND BETA II CENTER OF GRAVITY LIMITS FAA APPROVED: 22 FEB 2024 2-6 ROBINSON R22 SERIES 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 the roll. Flight prohibited with governor selected off, with exceptions for in-flight system malfunction or emergency procedures training. Flight in known icing conditions prohibited. Maximum operating density altitude 14,000 feet. Alternator, RPM governor, low rotor RPM warning system, and OAT gage must be operational for dispatch. Minimum crew is one pilot in the right seat. A flight instructor may act as pilot in command from the left seat. Solo flight from right seat only. Left seat belt must be buckled. Operation approved with either or both cabin doors removed. Loose items in cabin must be properly secured during doors-off flight. A functioning headset must be worn by each pilot. ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 20 JUN 2019 2-7 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 opera- tional. Orientation during night flight must be maintained by visual reference to ground objects illuminated solely by lights on the ground or adequate celestial illumination. Note: There may be additional requirements in countries outside the United States. FUEL LIMITATIONS APPROVED FUEL GRADES Grade Color Specification 100 Green ASTM D910 100LL Blue 100VLL Blue UL 91 Clear to Yellow (no dye) ASTM D7547 UL 94 HJELMCO 91/96 UL Clear to Yellow (no dye) Hjelmco Oil, Inc. Sollentuna, Sweden 91 Yellow TU 38.5901481-96 Ukrainian National Standard B91/115 Green GOST 1012-72 Russian National Standard B95/130 Amber ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 11 MAY 2020 2-8 FUEL LIMITATIONS (cont’d) FUEL CAPACITY Total Capacity US gallons (liters) Usable Capacity US gallons (liters) Tanks with bladders: Main tank 18.3 (69) 16.9 (64) Auxiliary tank 9.7 (37) 9.4 (36) Combined capacity 28.0 (106) 26.3 (100) Tanks without bladders: Main tank 19.8 (75) 19.2 (73) Auxiliary tank 10.9 (41) 10.5 (40) Combined capacity 30.7 (116) 29.7 (112) Note: Per R22 Service Bulletin SB-109A, fuel tanks without bladders should no longer be in service. INSTRUMENT MARKINGS AIRSPEED INDICATOR Green arc 50 to 102 KIAS Red line 102 KIAS ROTOR TACHOMETER Yellow arc 60 to 70% Lower red line 90 % Lower Yellow arc 90 to 101%* Green arc 101 to 104%* Upper Yellow arc 104 to 110% Upper red line 110% ENGINE TACHOMETER Yellow arc 60 to 70% Lower red arc 90 to 101%* Green arc 101 to 104%* Upper red arc 104 to 110% *R22s with O-320 engine may have tachometer with green arc from 97% to 104% RPM. ROBINSON MODEL R22 SECTION 2 LIMITATIONS INSTRUMENT MARKINGS {cont'd) OIL PRESSURE* Lower red line Lower yellow arc Green arc Upper yellow arc Upper red line 25 psi 25 to 55 psi 55 to 95 psi 95 to 115 psi 115 psi * Earlier gages show green arc from 60 to 90 psi and upper red line at 100 psi. OIL TEMPERATURE Green arc Red line 75t0245°f(24tO 118°C) 245°F (118°C) CYLINDER HEAD TEMPERATURE Green arc Red line MANIFOLD PRESSURE 200to500°F(93to 260°C) 500°F (260°C) Yellow arcs denote variable MAP limits. See placards on pages 2-10 and 2-11. Standard R22 (0-320-A2B or -A2C Engine) Yellow arc 23.2 to 25.9 in. Hg Red line 25.9 in. Hg HP and Alpha (0-320-82C Engine) Yellow arc 21.0 to 24.1 in. Hg Red line 24. 1 in. Hg Beta (0-320-B2C Engine) Yellow arc Red line Beta II (0-360-J2A Engine) Yellow arc Red line 21.0 to 25.2 in. Hg 25.2 in. Hg 19.6 to 24.1 in. Hg 24.1 in. Hg CARBURETOR AIR TEMPERATURE Yellow arc -15 to 5°C FAA APPROVED: 1 JUL 2005 2-9 ROBINSON MODEL R22 PLACARDS SECTION 2 LIMITATIONS In clear view and readable by pilot in flight: 26 LIMIT MANIFOLD PRESSURE Standard R22 MAP. 0-320-A2B or 25 /:-. + . '~ A2C Engine IN. ()-. 24 ,< HG. 23 0 1 2 3 4 5 6 PRESSURE ALT. 1000 FEET LIMIT MANIFOLD PRESSURE R22 HP and Alpha 0-320-B2C Engine MAP. R22 Beta IN. 221---+--+==::::..+....::::::-+-~-F-~ HG. 21t---+--+--t---+--+---+--+-'...,-f 0 1 2 3 4 5 6 PRESSUREALT.1000 FEET LIMIT MANIFOLD PRESSURE 5 MINUTE TAKEOFF RATING 7 8 0-320-B2C Engine 25 ORMCP BTRACT INCH MAP. MAP. 24t-:::::'.""T'"-T"=-t---=::::--f",r:- IN. HG. 221---+-~=--l---+--+---!=~i-=:::::--f 0 1 2 3 4 5 6 7 8 PRESSURE ALT. 1000 FEET FAA APPROVED: 13 OCT 2000 2-10 FAA APPROVED: 13 OCT 2000 2-11 ROBINSON MODEL R22 SECTION 2 LIMITATIONS PLACARDS (cont’d) R22 Beta II O-360-J2A Engine All R22s except Beta II R22 Beta II ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 20 JUN 2019 2-12 PLACARDS (cont’d) Near main fuel tank filler cap: FUEL 100 OCT MIN GRADE AVIATION GASOLINE or FUEL 91/96 MIN GRADE AVIATION GASOLINE or FUEL AVIATION GASOLINE – GRADE 100LL OR SEE PILOT’S HANDBOOK or R22s with O-320-A2B or -A2C engine may have: FUEL 80/87 MIN GRADE AVIATION GASOLINE Near aux fuel tank filler cap: AUX FUEL 100 OCT MIN GRADE AVIATION GASOLINE or AUX FUEL 91/96 MIN GRADE AVIATION GASOLINE or AUX FUEL AVIATION GASOLINE – GRADE 100LL OR SEE PILOT’S HANDBOOK ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 26 OCT 2016 2-13 PLACARDS (cont’d) Near shut-off valve: FUEL ON OFF Near main tank fuel gage: For bladder-style tank 16.9 US GAL For aluminum (non-bladder) tank 19.2 US GAL Near aux tank fuel gage: For bladder-style tank AUX 9.4 US GAL For aluminum (non-bladder) tank AUX 10.5 US GAL In clear view of both occupants: NO SMOKING In clear view of pilot (Alpha, Beta, and Beta II with aft battery installations): MINIMUM SOLO PILOT WEIGHT 130 LB (135 LB WITH FULL AUX FUEL) or SEE PILOT’S HANDBOOK FOR SOLO PILOT WEIGHT LESS THAN 135 LB (61KG) ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 26 OCT 2016 2-14 PLACARDS (cont’d) In clear view of pilot: THIS ROTORCRAFT APPROVED FOR DAY AND NIGHT VFR OPERATIONS LOW-G PUSHOVERS PROHIBITED On left-hand cyclic: SOLO FROM RIGHT SEAT ONLY On or near collective controls: NO STOWAGE KEEP AREA CLEAR Inside each baggage compartment: CAUTION DO NOT EXCEED ANY OF THE FOLLOWING: • COMPARTMENT CAPACITY: 50 LB MAX • COMBINED SEAT PLUS COMPARTMENT: 240 LB MAX • ROTORCRAFT GROSS WEIGHT LIMIT SEE ROTORCRAFT FLIGHT MANUAL FOR ADDITIONAL INSTRUCTIONS On carburetor air temperature gage: CAUTION BELOW 18 IN. MP, IGNORE GAGE & APPLY FULL CARB HEAT Near heater push-pull control when heater is installed: IN CASE OF ENGINE FIRE PUSH HEATER CONTROL TO OFF ROBINSON R22 SERIES SECTION 2 LIMITATIONS FAA APPROVED: 20 JUN 2019 2-15 INFORMATION PER FAA AD 95-26-04 The following limitations (1-3) are to be observed unless the pilot manipulating the controls has logged 200 or more flight hours in helicopters, at least 50 of which must be in the RHC Model R22 helicopter, and has completed the awareness training specified in Special Federal Aviation Regulation (SFAR) No. 73, issued February 27, 1995. 1. Flight when surface winds exceed 25 knots, including gusts, is prohibited. 2. Flight when surface wind gust spreads exceed 15 knots is prohibited. 3. Continued flight in moderate, severe, or extreme turbulence is prohibited. Adjust forward airspeed to between 60 knots indicated airspeed (KIAS) and 0.7 V ne but no lower than 57 KIAS, upon inadvertently encountering moderate, severe, or extreme turbulence. Note: Moderate turbulence is turbulence that causes: (1) changes in altitude or attitude; (2) variations in indicated airspeed; and (3) aircraft occupants to feel definite strains against seat belts. RHC NOTE This AD is issued by the FAA and is applicable to US-registered helicopters. INTENTIONALLY BLANK FAA APPROVED: 11 MAY 2020 3-i SECTION 3 EMERGENCY PROCEDURES CONTENTS Page Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Power Failure - General . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Power Failure Above 500 Feet AGL . . . . . . . . . . . . . . . . 3-2 Power Failure Between 8 Feet and 500 Feet AGL . . . . . 3-2 Power Failure Below 8 Feet AGL . . . . . . . . . . . . . . . . . . 3-3 Maximum Glide Distance Configuration . . . . . . . . . . . . . 3-3 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 on Ground . . . . . . . . . . . . . . . . 3-6 Engine Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Electrical Fire in Flight . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6 Tachometer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Governor Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7 Warning/Caution Lights . . . . . . . . . . . . . . . . . . . . . . . . . 3-8 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-10 Information per FAA AD 95-26-04 . . . . . . . . . . . . . . . . 3-11 ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES INTENTIONALLY BLANK FAA APPROVED: 26 OCT 2016 3-1 SECTION 3 EMERGENCY PROCEDURES DEFINITIONS Land Immediately - Land on the nearest clear area where a safe normal landing can be performed. Be prepared to enter autorotation during approach, if required. Land as soon as practical - Landing site is at pilot’s discretion based on nature of problem and available landing areas. Flight beyond nearest airport is not recommended. POWER FAILURE - GENERAL A power failure may be caused by either an engine or drive system failure and will usually be indicated by the low RPM horn. An engine failure may be indicated by a change in noise level, nose left yaw, an oil pressure light, or decreasing engine RPM. A drive system failure may be indicated by an unusual noise or vibration, nose right or left yaw, or decreasing rotor RPM while engine RPM is increasing. In case of power failure, immediately lower collective to enter autorotation. 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 R22 SERIES SECTION 3 EMERGENCY PROCEDURES POWER FAILURE ABOVE 500 FEET AGL 1. Lower collective immediately to maintain rotor RPM. 2. Establish a steady glide at approximately 65 KIAS. (For maximum glide distance, see page 3-3.) 3. Adjust collective to keep RPM between 97 and 110% or apply full down collective if light weight prevents attaining above 97%. 4. Select landing spot and, if altitude permits, maneuver so landing will be into wind. 5. A restart may be attempted at pilot’s discretion if sufficient time is available (See “Air Restart Procedure”, page 3-3). 6. If unable to restart, turn unnecessary switches and fuel valve off. 7. At about 40 feet AGL, begin cyclic flare to reduce rate of descent and forward speed. 8. At about 8 feet AGL, apply forward cyclic to level ship and raise collective just before touchdown to cushion landing. Touch down in level attitude with nose straight ahead. POWER FAILURE BETWEEN 8 FEET AND 500 FEET AGL 1. Lower collective immediately to maintain rotor RPM. 2. Adjust collective to keep RPM between 97 and 110% or apply full down collective if light weight prevents attaining above 97%. 3. Maintain airspeed until ground is approached, then begin cyclic flare to reduce rate of descent and forward speed. 4. At about 8 feet AGL, apply forward cyclic to level ship and raise collective just before touchdown to cushion landing. Touch down in level attitude and nose straight ahead. FAA APPROVED: 21 FEB 2014 3-2 ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES ROBINSON MODEL R22 SECTION 3 EMERGENCY PROCEDURES POWER FAILURE BELOW 8 FEET AGL 1. Apply right pedal as required to prevent yawing. 2. Allow aircraft to settle. 3. Raise collective just before touchdown to cushion landing. MAXIMUM GLIDE DISTANCE CONFIGURATION 1. Airspeed approximately 75 KIAS. 2, Rotor RPM approximately 90%. 3. Best glide ratio is about 4: 1 or one nautical mile per 1500 feet AGL. CAUTION Increase rotor RPM to 97% minimum when autorotating below 500 feet AGL AIR RESTART PROCEDURE 1. Mixture - full rich. 2. Primer (if installed) - down and locked. 3. Throttle - closed, then cracked slightly. 4. Actuate starter with left hand. CAUTION Do not attempt restart if engine malfunction is suspected or before safe autorotation is established. FAA APPROVED: 6 JULY 1995 3-3 ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 21 FEB 2014 3-4 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. Passenger exit aircraft. 4. Fly to safe distance from passenger to avoid possible injury by rotors. 5. Switch battery and alternator OFF. 6. Roll throttle off into overtravel spring. 7. Keep aircraft level and apply full collective as aircraft contacts water. 8. Apply lateral cyclic to stop rotors. 9. Release seat belt and quickly clear aircraft when rotors stop. FAA APPROVED: 11 MAY 2020 3-5 LOSS OF TAIL ROTOR THRUST IN FORWARD FLIGHT Failure is usually indicated by nose right yaw which cannot be corrected by applying left pedal. 1. Immediately enter autorotation. 2. Maintain at least 70 KIAS if practical. 3. Select landing site, roll throttle off into overtravel spring, and perform autorotation landing. NOTE When a suitable landing site is not available, the vertical stabilizers may permit limited controlled flight at low power settings and airspeeds above 70 KIAS; however, prior to reducing airspeed, enter full autorotation. LOSS OF TAIL ROTOR THRUST IN HOVER Failure is usually indicated by nose right yaw which cannot be stopped by applying left pedal. 1. Immediately roll throttle off into overtravel spring and allow aircraft to settle. 2. Raise collective just before touchdown to cushion landing. 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 R22 SERIES SECTION 3 EMERGENCY PROCEDURES ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 26 OCT 2016 3-6 ENGINE FIRE DURING START ON GROUND 1. Cranking – Continue and attempt to start which would suck flames and excess fuel into engine. 2. If engine starts, run at 50-60% RPM for a short time. 3. Fuel mixture – OFF. 4. Fuel valve – OFF. 5. Battery switch – OFF. 6. If time permits, apply rotor brake to stop rotors. 7. Exit helicopter. ENGINE FIRE IN FLIGHT 1. Enter autorotation. 2. Cabin heat – OFF (if installed and time permits). 3. Cabin vent – ON (if time permits). 4. If engine is running, perform normal landing, then fuel mixture OFF and fuel valve OFF. If engine stops running, fuel valve OFF and complete autorotation landing. 5. Battery switch – OFF. 6. If time permits, apply rotor brake to stop rotors. 7. Exit helicopter. ELECTRICAL FIRE IN FLIGHT 1. Battery and alternator switches – OFF. 2. Open cabin vents. 3. Land immediately. 4. Fuel mixture OFF and fuel valve OFF. 5. If time permits, apply rotor brake to stop rotors. 6. Exit helicopter. CAUTION Low RPM warning system and governor are inoperative with battery and alternator switches both off. ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 20 JUN 2019 3-7 TACHOMETER FAILURE If rotor or engine tach malfunctions in flight, use remaining tach to monitor RPM. If it is not clear which tach is malfunctioning or if both tachs malfunction, allow governor to control RPM and land as soon as practical. NOTE Each tach, the governor, and the low RPM horn are on separate power circuits. A special circuit allows the battery to supply power to the tachs with the battery and alternator switches both off. GOVERNOR FAILURE If engine RPM governor malfunctions, grip throttle firmly to override the governor, then switch governor off. Complete flight using manual throttle control. WARNING/CAUTION LIGHTS NOTE If a light causes excessive glare at night, bulb may be unscrewed or circuit breaker pulled to eliminate glare during landing. OIL Indicates loss of engine power or oil pressure. Check engine tach for power loss. Check oil pressure gage and, if pressure loss is confirmed, land immediately. Continued operation without oil pressure will cause serious engine damage and engine failure may occur. MR TEMP Indicates excessive temperature of main rotor gearbox. See note below. MR CHIP Indicates metallic particles in main rotor gearbox. See note below. TR CHIP Indicates metallic particles in tail rotor gearbox. See note below. NOTE If 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 rotor gearbox must be refilled with new oil). Hover for at least 30 minutes. If chip light comes on again, replace gearbox before further flight. ROBINSON MODEL R22 SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 13 OCT 2000 3-8 ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 26 OCT 2016 3-9 WARNING/CAUTION LIGHTS (cont’d) LOW FUEL Indicates approximately one gallon of usable fuel remaining for all-aluminum fuel tanks or 1.5 gallons for bladder-style tanks. The engine will run out of fuel after approximately five minutes at cruise power for aircraft with all-aluminum tanks or ten minutes with bladder-style tanks. CAUTION Do not use low fuel caution light as a working indication of fuel quantity. CLUTCH Indicates clutch actuator circuit is on, either engaging or disengaging clutch. When switch is in the ENGAGE position, light stays on until belts are properly tensioned. Never take off before light goes out. NOTE Clutch light may come on momentarily during run-up or during flight to retension belts as they warm-up and stretch slightly. This is normal. If, however, the light flickers or comes on in flight and does not go out within 10 seconds, pull CLUTCH circuit breaker and land as soon as practical. Reduce power and land immediately if there are other indications of drive system failure (be prepared to enter autorotation). Have drive system inspected for a possible malfunction. ALT Indicates low voltage and possible alternator failure. Turn off nonessential electrical equipment and switch ALT off and back on after one second to reset alternator control unit. If light stays on, land as soon as practical. Continued flight without functioning alternator can result in loss of power to tachometers, producing a hazardous flight condition. WARNING/CAUTION LIGHTS (cont’d) STARTER ON Indicates starter motor is engaged. If light does not go out when ignition switch is released from start position, immediately pull mixture off and turn battery switch off. Have starter motor serviced. LOW RPM Indicates rotor speed below 97% RPM. To restore RPM, immediately lower collective, roll throttle on and, in forward flight, apply aft cyclic. Light is disabled when collective is full down. GOV OFF Indicates engine RPM governor is switched off. CARBON MONOXIDE (if installed) Indicates elevated levels of carbon monoxide (CO) in cabin. Shut off heater and open nose and door vents. If hovering, land or transition to forward flight. If symptoms of CO poisoning (headache, drowsiness, dizziness) accompany light, land immediately. BRAKE Indicates rotor brake is engaged. Release immediately in flight or before starting engine. FULL THROTTLE (if installed) Indicates engine near full throttle. The governor will be ineffective because it cannot increase throttle to maintain RPM. Lower collective as required to extinguish light. AUDIO ALERTS LOW RPM HORN Horn is provided by a speaker in the side of the instrument console on earlier aircraft or through the audio system on later aircraft. The horn activates simultaneously with the LOW RPM caution light and indicates rotor speed below 97% RPM. To restore RPM, lower collective, roll throttle on and, in forward flight, apply aft cyclic. Horn and Light are disabled when collective is full down. FAA APPROVED: 11 MAY 2020 3-10 ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES ROBINSON R22 SERIES SECTION 3 EMERGENCY PROCEDURES FAA APPROVED: 11 MAY 2020 3-11 AUDIO ALERTS (Cont’d) HIGH RPM WARBLE On later aircraft, a warble (high/low tone) in the audio system indicates rotor speed is approaching 110% RPM limit. Raise collective as required to control RPM. INFORMATION PER FAA AD 95-26-04 1) RIGHT ROLL IN LOW “G” CONDITION Gradually apply aft cyclic to restore positive “G” forces and main rotor thrust. Do not apply lateral cyclic until positive “G” forces have been established. 2) UNCOMMANDED PITCH, ROLL. OR YAW RESULTING FROM FLIGHT IN TURBULENCE. Gradually apply controls to maintain rotor RPM, positive “G” forces, and to eliminate sideslip. Minimize cyclic control inputs in turbulence; do not overcontrol. 3) INADVERTENT ENCOUNTER WITH MODERATE, SEVERE, OR EXTREME TURBULENCE. If the area of turbulence is isolated, depart the area; otherwise, land the helicopter as soon as practical. INTENTIONALLY BLANK FAA APPROVED: 26 OCT 2016 4-i SECTION 4 NORMAL PROCEDURES CONTENTS Page Recommended Airspeeds . . . . . . . . . . . . . . . . . . . . . . . 4-1 Daily or Preflight Checks . . . . . . . . . . . . . . . . . . . . . . . . 4-1 Before Starting Engine . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 Starting Engine and Run-Up . . . . . . . . . . . . . . . . . . . . . . 4-7 Takeoff Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-8 Doors-Off Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9 Practice Autorotation – Power Recovery . . . . . . . . . . . . 4-9 Practice Autorotation – With Ground Contact . . . . . . . . 4-10 Use of Carburetor Heat . . . . . . . . . . . . . . . . . . . . . . . . . 4-11 Use of Carb Heat Assist . . . . . . . . . . . . . . . . . . . . . . . . . 4-11 Descent, Approach, and Landing . . . . . . . . . . . . . . . . . . 4-12 Shutdown Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-13 Noise Abatement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-14 Information per FAA AD 95-26-04 . . . . . . . . . . . . . . . . 4-15 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES INTENTIONALLY BLANK SECTION 4 NORMAL PROCEDURES RECOMMENDED AIRSPEEDS Takeoff and Climb 60 KIAS Maximum Rate of Climb (VY ) 53 KIAS Maximum Range 83 KIAS* Significant Turbulence 60 to 70 KIAS* Landing Approach 60 KIAS Autorotation 60 to 70 KIAS* * Certain conditions may require lower airspeed. See Vne placards in Section 2. DAILY OR PREFLIGHT CHECKS Remove ground handling wheels and all covers and tiedowns. Remove even small accumulations of frost, ice, or snow, especially from rotor blades. Check maintenance records to verify aircraft is airworthy. Check general condition of aircraft and verify no visible damage, fluid leakage, or abnormal wear. Verify no fretting at rivets and seams where parts are joined together. Fretting of aluminum parts produces a fine black powder while fretting of steel parts produces a reddish-brown or black residue. Verify Telatemps show no temperature increase that cannot be attributed to a change in operating conditions (mechanics draw a reference line to the right of the highest temperature square which has darkened in operation). Verify torque stripes on critical fasteners are not broken or missing. FAA APPROVED: 11 MAY 2020 4-1 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 17 NOV 2021 4-2 DAILY OR PREFLIGHT CHECKS (cont’d) 1. Cowl Doors Battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Oil pressure and alternator lights . . . . . . . . . . . . . . . . ON Warning light test switches . . . . . . . . . . . . . Push to test EMU (if installed) . . . . . . . . . . . . . . . . . . . . . . . Check status Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . Check gages Battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Aux fuel tank quantity . . . . . . . . . . . . . . . . . . . . . Check Fuel filler cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tight Aux fuel tank . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Fuel lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Fuel tank sump drain(s) . . . . . . . . . . . . . . . . . . . Sample Gearbox oil . . . . . . . . . . . . . . . . . . . . . . . . Full, no leaks Rotor brake . . . . . . . . . . . . . . . . . . . . Actuation normal Flex coupling . . . . . . . . . . . . . . . . No cracks, nuts secure Yoke flanges . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Gearbox Telatemp . . . . . . . . . . . . . . . . . . . . . . . Normal Sprag clutch . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Static source . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Control rod ends . . . . . . . . . . . . Free without looseness Steel tube frame . . . . . . . . . . . . . . . . . . . . . . No cracks All fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Tail rotor control . . . . . . . . . . . . . . . . . . No interference Cowl doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . Latched 2. Engine Right Side Carb air ducts . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Carb heat scoop . . . . . . . . . . . . . . . . . . . . . . . . . Secure Engine sheet metal . . . . . . . . . . . . . . . . . . . . . No cracks Electrical terminals . . . . . . . . . . . . . . . . . . . . . . . . Tight Fuel line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Oil cooler door . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Oil lines . . . . . . . . . . . . . . . . . . . . . . No leaks or chafing Exhaust system . . . . . . . . . . . . . . . . . . . . . . . No cracks Engine general condition . . . . . . . . . . . . . . . . . . . Check V-belt condition . . . . . . . . . . . . . . . . . . . . . . . . . . Check V-belt slack . . . . . . . . . . . . 1.5 inches (4 cm) maximum Sprag clutch . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Upper bearing . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Telatemp – upper bearing . . . . . . . . . . . . . . . . . . Normal ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-3 DAILY OR PREFLIGHT CHECKS (cont’d) 2. Engine Right Side (cont’d) Upper Sheave Condition . . . . . . . . . . . . . . . . . . . . Check Lower sheave groove wear . . . . . . . . Smooth & Uniform Flex coupling . . . . . . . . . . . . . . . . No cracks, nuts secure Yoke flanges . . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Steel tube frame . . . . . . . . . . . . . . . . . . . . . . . No cracks Tail rotor control . . . . . . . . . . . . . . . . . . . No interference 3. Engine Rear Cooling fan nut . . . . . . . . . . . . . . . Pin in line with marks Cooling fan . . . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Fan scroll . . . . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Teletemps – lower bearing . . . . . . . . . . . . . . . . . Normal Lower bearing . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks 4. Empennage Tail surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . No cracks Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Position light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check 5. Tail Rotor Gearbox Telatemp . . . . . . . . . . . . . . . . . . . . . . . . Normal Gearbox . . . . . . . . . . . . . . . . . . . . . . Oil visible, no leaks Blades . . . . . . . . . . . . . . . . Clean and no damage/cracks Pitch links . . . . . . . . . . . . . . . . . . . . . . . . . No looseness Teeter bearings . . . . . . . . . . . . . . . . . . . Check condition Teeter bearing bolt . . . . . . . . . . . . . . . . . Does not rotate Control bellcrank . . . . . . . . . . . . . Free without looseness 6. Tailcone Skins . . . . . . . . . . . . . . . . . . . . . . . . . No cracks or dents Strobe light condition . . . . . . . . . . . . . . . . . . . . . . Check Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-4 DAILY OR PREFLIGHT CHECKS (cont’d) 7. Engine Left Side Engine oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 qt Oil filter (if installed) . . . . . . . . . . . . . . . Secure, no leaks Fuel lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No leaks Gascolator drain . . . . . . . . . . . . . . . . . . . . . . . . . Sample Throttle linkage . . . . . . . . . . . . . . . . . . . . . . . . Operable Battery and relay (if located here) . . . . . . . . . . . . Secure Alternator belt tension . . . . . . . . . . . . . . . . . . . . . Check Steel tube frame . . . . . . . . . . . . . . . . . . . . . . . No cracks Engine sheet metal . . . . . . . . . . . . . . . . . . . . . No cracks Exhaust system . . . . . . . . . . . . . . . . . . . . . . . No cracks Engine general condition . . . . . . . . . . . . . . . . . . . . Check 8. Main Fuel Tank Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Filler cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tight Leakage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . None 9. Main Rotor CAUTION Do not pull down on blades to teeter rotor. To lower a blade, push up on opposite blade. Blades . . . . . . . . . . . . . . . . Clean and no damage/cracks CAUTION Verify erosion on lower surface of blades has not exposed skin-to-spar bond line. Reference Rotor Systems description in Section 7. Pitch change boots . . . . . . . . . . . . . . . . . . . . . No leaks Main hinge bolts . . . . . . . . . . . . . . . Cotter pins installed All rod ends . . . . . . . . . . . . . . . . Free without looseness All fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . Secure Swashplate scissors . . . . . . . . . No excessive looseness DAILY OR PREFLIGHT CHECKS (cont’d) 10. Fuselage Left Side Baggage compartment . . . . . . . . . . . . . . . . . . Check Removable controls . . . . . . . . . . . . Secure if installed Collective control . . . . . . . . . . . . . . . . . . . . . . Clear Seat Belt . . . . . . . . . . . Check condition and fastened Door . . . . . . . . . . . . . . . . . . . . Unlocked and latched Door hinge safety pins . . . . . . . . . . . . . . . . . Installed Landing gear . . . . . . . . . . . . . . . . . . . . . . . . . Check Position light . . . . . . . . . . . . . . . . . . . . . . . . . Check 11. Nose Section Pitot tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Windshield condition and cleanliness . . . . . . . . Check Landing lights . . . . . . . . . . . . . . . . . . . . . . . . Check Yaw string . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check 12. Fuselage Right Side Landing gear . . . . . . . . . . . . . . . . . . . . . . . . . Check Position light . . . . . . . . . . . . . . . . . . . . . . . . . Check Door hinge safety pins . . . . . . . . . . . . . . . . . Installed Baggage compartment . . . . . . . . . . . . . . . . . . Check 13. Cabin Interior Loose articles . . . . . . . . . . . . . . . Removed or stowed Seat belt . . . . . . . . . . . . . . . . . . . . . Check condition Instruments, switches, and controls . . Check condition Clock . . . . . . . . . . . . . . . . . . . . . . . . . . Functioning CAUTION For helicopters with removable con- trols, remove left seat controls if per- son in that seat is not a rated helicopter pilot. CAUTION Be sure rotor blades are approximately level to avoid possible tailcone strike. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-5 DAILY OR PREFLIGHT CHECKS (cont’d) CAUTION When flying solo, fill left baggage compartment to capacity before using right compartment. Avoid placing objects in compartments which could injure occupant if seat collapses during a hard landing. CAUTION Shorter pilots may require cushion to obtain full travel of all controls. Verify aft cyclic travel is not restricted. BEFORE STARTING ENGINE Seat belts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fastened Fuel shut-off valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Cyclic, collective, pedals . . . . . . . . . . . . . . . Full travel free Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . Full travel free Collective . . . . . . . . . . . . . . . . . . . . . Full down, friction ON Cyclic . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral, friction ON Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Neutral Rotor brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengaged Circuit breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . In Carb heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mixture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Full rich Mixture guard* . . . . . . . . . . . . . . . . . . . . . . . . . . . Installed Primer (if installed) . . . . . . . . . . . . . . . . . . Down and locked Landing lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Avionics switch (if installed) . . . . . . . . . . . . . . . . . . . . . OFF Clutch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengaged Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Set Governor switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON * Mixture guard is not used on aircraft with vernier mixture control on console face. FAA APPROVED: 21 FEB 2014 4-6 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES STARTING ENGINE AND RUN-UP Throttle twists for priming . . . . . . . . . . . . . . . . As required Throttle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Closed Battery, strobe switches . . . . . . . . . . . . . . . . . . . . . . . . ON Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clear Ignition switch . . . . . . . . . . . . . . . . . . . . . . Start, then Both Starter-On light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Set engine RPM . . . . . . . . . . . . . . . . . . . . . . . . . 50 to 60% Clutch switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engaged Blades turning . . . . . . . . . . . . . . . . . . . Less than 5 seconds Alternator switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Oil pressure within 30 seconds . . . . . . . . . 25 psi minimum Avionics, headsets . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Audio alert (if equipped) . . . . . . . . . . . . . . . . . . . . . . . . Test Wait for clutch light out . . . . . . . . . . . . . Circuit breakers in Warm-up RPM . . . . . . . . . . . . . . . . . . . . . . . . . . 70 to 75% Engine gages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Green Mag drop at 75% RPM . . . . . . . . . . . 7% max in 2 seconds Carb heat . . . . . . . . . . . . . . . CAT rise/drop, set as required Sprag clutch check . . . . . . . . . . . . . . . . . . . . . Needles split Doors (if installed) . . . . . . . . . . . . . . . . . Closed and latched Limit MAP chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . Check Cyclic/collective friction . . . . . . . . . . . . . . . . . . . . . . . . OFF Governor On, increase throttle . . . . . . . . . . RPM 102-104% Warning lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Out Lift collective slightly, reduce RPM . . . . . Horn/light at 97% CAUTION For aircraft which provide low RPM horn through the audio system, a headset for each pilot is required to hear the horn. CAUTION Avoid continuous operation at rotor speed of 60 to 70% to minimize tail resonance. CAUTION On slippery surfaces, be prepared to counter nose-right rotation with left pedal as governor increases RPM. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-7 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 OCT 2016 4-8 TAKEOFF PROCEDURE 1. Verify doors latched, governor ON, and RPM stabilized at 102 to 104%. 2. Clear area. Slowly raise collective until aircraft is light on skids. Reposition cyclic as required for equilibrium, then gently lift aircraft into hover. 3. Check gages in green and adjust carb heat if required. 4. Lower nose and accelerate to climb speed following profile shown by height-velocity diagram in Section 5. If RPM drops below 102%, lower collective. CRUISE 1. Adjust carb heat if required. (See page 4-11.) 2. Verify RPM near top of green arc. 3. Set manifold pressure as desired with collective. Observe MAP and airspeed limits. 4. Pull RT TRIM knob. 5. Verify gages in green, warning lights out. CAUTION In turbulence, reduce power and use a slower than normal cruise speed. If turbulence is significant or becomes uncomfortable for the pilot, use 60 to 70 KIAS. CAUTION Exercise extreme care never to inadvertently pull mixture control as engine stoppage will result. CAUTION In-flight leaning with engine mixture control is not recommended. Engine stoppage may result as there is no propeller to keep engine turning should overleaning occur. FAA APPROVED: 20 JUN 2019 4-9 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES DOORS-OFF OPERATION Avoid removing left door to protect tail rotor from loose objects. If left door must be removed, warn passenger to secure loose objects and to keep head and arms inside cabin to avoid high velocity airstream. PRACTICE AUTOROTATION – POWER RECOVERY 1. Adjust carb heat if required. (See page 4-11.) 2. Lower collective to down stop and reduce throttle as desired for tachometer needle separation. CAUTION To avoid inadvertent engine stoppage, do not chop throttle to simulate a power failure. Always roll throttle off smoothly. Recover immediately if engine is rough or engine RPM continues to drop. NOTE Governor is inactive below 80% engine RPM regardless of governor switch position. NOTE When entering autorotation from above 4000 feet, reduce throttle slightly before lowering collective to prevent engine overspeed. 3. Adjust collective to keep rotor RPM within limits and adjust throttle for tachometer needle separation. 4. Keep airspeed 60 to 70 KIAS. 5. At about 40 feet AGL, begin cyclic flare to reduce rate of descent and forward speed. 6. At about 8 feet AGL, apply forward cyclic to level aircraft and raise collective to control descent. Add throttle if required to keep RPM in green arc. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 JUN 2012 4-10 PRACTICE AUTOROTATION - POWER RECOVERY (Cont’d) CAUTION Simulated engine failures require prompt lowering of collective to avoid dangerously low rotor RPM. Catastrophic rotor stall could occur if the rotor RPM ever drops below 80% plus 1% per 1000 feet of altitude. PRACTICE AUTOROTATION - WITH GROUND CONTACT If practice autorotations with ground contact are required for demonstration purposes, perform in same manner as power recovery autorotations except: Prior to cyclic flare, roll throttle off into overtravel spring and hold it against hard stop until autorotation is complete. (This prevents throttle correlator from adding power when collective is raised.) Always contact ground with skids level and nose straight ahead. CAUTION The R22 has a light, low-inertia rotor system. Most of the energy required for an autorotation is stored in the forward momentum of the aircraft, not in the rotor. Therefore, a well- timed cyclic flare is required and rotor RPM must be kept in the green until just before ground contact. NOTE Have landing gear skid shoes inspected frequently when practicing autorotations with ground contact. Rapid wear of skid shoes may occur. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 JUN 2012 4-11 USE OF CARBURETOR HEAT Carburetor ice can form in a wide range of atmospheric conditions, but is most likely to form when OAT is between -4ºC and 30ºC (25ºF and 86ºF) and the difference between OAT and dew point is less than 15Cº (27Fº). When conditions conducive to carburetor ice are suspected, use carburetor heat as follows: During Run-up: Use full carburetor heat (it is filtered) during warm-up to preheat induction system. During Takeoff, Climb, and Cruise: Use carb heat as required to keep CAT gage indication out of yellow arc. During Descent and Autorotation: At power settings below 18 inches MAP, apply full carb heat regardless of CAT gage indication. CAT gage does not indicate correct carburetor temperature below 18 inches MAP. CAUTION The pilot may be unaware of carburetor ice formation as the governor will automatically increase throttle and maintain constant manifold pressure and RPM. Therefore, the pilot must apply carburetor heat as required whenever icing conditions are suspected. USE OF CARB HEAT ASSIST A carburetor heat assist device is installed on R22s with O-360 engines. The carb heat assist correlates application of carburetor heat with changes in collective setting to reduce pilot work load. Lowering collective mechanically adds heat and raising collective reduces heat. A friction clutch allows the pilot to override the system and increase or decrease heat as required. A latch is provided at the control knob to lock carburetor heat off. The knob should be left unlatched unless it is obvious that conditions are not conducive to carburetor ice. Apply carburetor heat as required if carburetor ice is a possibility. Monitor CAT gage and readjust as necessary following lift to hover or any power change. FAA APPROVED: 26 OCT 2016 4-12 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES DESCENT, APPROACH, AND LANDING 1. Reduce power with collective as desired. Adjust carb heat as required. Observe airspeed limits. CAUTION Do not initiate a descent with forward cyclic. This can produce a low-G condition. Always initiate a descent by lowering collective. 2. Make final approach into wind at lowest practical rate of descent with initial airspeed of 60 knots. 3. Reduce airspeed and altitude smoothly to hover. (Be sure rate of descent is less than 300 FPM before airspeed is reduced below 30 KIAS.) 4. From hover, lower collective gradually until ground contact. 5. After initial ground contact, lower collective to full down position. CAUTION When landing on a slope, return cyclic control to neutral before reducing rotor RPM. CAUTION Never leave helicopter flight controls unattended while engine is running. CAUTION Hold throttle closed if passenger is entering or exiting with engine running and left seat collective installed. SHUTDOWN PROCEDURE Collective down, RPM 70-75% . . . . . . . . . . . . . Friction ON Cyclic and pedals neutral . . . . . . . . . . . . . . . . . Friction ON CHT drop . . . . . . . . . . . . . . . . . . . . . . . . . . Throttle closed Clutch switch . . . . . . . . . . . . . . . . . . . . . . . . . . . Disengage Wait 30 seconds . . . . . . . . . . . . . . . . . . . . . . . Mixture OFF Mixture guard . . . . . . . . . . . . . . . . . . . . . . Back on mixture Wait 30 seconds . . . . . . . . . . . . . . . . . . . Apply rotor brake Clutch light . . . . . . . . . . . . . . . . . . . . . . . . . . . . Extinguishes Avionics, alt, battery, and ignition switches . . . . . . . . . OFF NOTE If ambient temperature is above 100°F (38°C), cool down at 70-75% RPM for at least one minute before reducing to idle. NOTE During idle and after engine shutdown, pilot should uncover one ear and listen for unusual noise which may indicate impending failure of a bearing or other component. CAUTION Do not slow rotor by raising collective during shutdown. Blades may flap and strike tailcone. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 11 MAY 2020 4-13 ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES FAA APPROVED: 26 JUN 2012 4-14 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 usually occurs during shallow high-speed descents, especially during turns. It can be avoided by using slower, steeper descents. With the right door removed, 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 instructions or when, in the pilot’s judgment, they would result in an unsafe flight path. ROBINSON R22 SERIES SECTION 4 NORMAL PROCEDURES INFORMATION PER FAA AD 95-26-04 Until the FAA completes its research into the conditions and aircraft characteristics that lead to main rotor blade/ fuselage contact accidents, and corrective type design changes and operating limitations are identified, Model R22 pilots are strongly urged to become familiar with the following information and comply with these recommended procedures: Main Rotor Stall: Many factors may contribute to main rotor stall and pilots should be familiar with them. Any flight condition that creates excessive angle of attack on the main rotor blades can produce a stall. Low main rotor RPM, aggressive maneuvering, high collective angle (often the result of high-density altitude, over-pitching [exceeding power available] during climb, or high forward airspeed) and slow response to the low main rotor RPM warning horn and light may result in main rotor stall. The effect of these conditions can be amplified in turbulence. Main rotor stall can ultimately result in contact between the main rotor and airframe. Additional information on main rotor stall is provided in the Robinson Helicopter Company Safety Notices SN-10, SN-15, SN-20, SN-24, SN-27, and SN-29. Mast Bumping: Mast bumping may occur with a teetering rotor system when excessive main rotor flapping results from low "G" (load factor below 1.0) or abrupt control input. A low "G" flight condition can result from an abrupt cyclic pushover in forward flight. High forward airspeed, turbulence, and excessive sideslip can accentuate the adverse effects of these control movements. The excessive flapping results in the main rotor hub assembly striking the main rotor mast with subsequent main rotor system separation from the helicopter. To avoid these conditions, pilots are strongly urged to follow these recommendations: 1) Maintain cruise airspeeds between 60 KIAS and less than 0.9 VNE' but no lower than 57 KIAS. 2) Use maximum "power-on" RPM at all times during powered flight. 3} Avoid sideslip during flight. Maintain in-trim flight at all times. 4) Avoid large, rapid forward cyclic inputs in forward flight, and abrupt control inputs in turbulence. FAA APPROVED: 26 JUN 2012 4-15 INTENTIONALLY BLANK ROBINSON R22 SERIES SECTION 5 GENERAL FAA APPROVED: 22 FEB 2024 5-i SECTION 5 PERFORMANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Demonstrated Operating Temperature . . . . . . . . . . . . . 5-1 Airspeed Calibration . . . . . . . . . . . . . . . . . . 5-2 Density Altitude Chart . . . . . . . . . . . . . . . . . . 5-3 IGE Hover Ceiling Vs Gross Weight R22 Standard . . . . . . . . . . . . . . . . . . . . . . . . . 5-4 R22 HP, Alpha, and Beta . . . . . . . . . . . . . . . . . 5-5 R22 Beta II. . . . . . . . . . . . . . . . . . . . . . . . . . 5-6 OGE Hover Ceiling Vs Gross Weight R22 Standard . . . . . . . . . . . . . . . . . . . . . . . . . 5-7 R22 HP and Alpha . . . . . . . . . . . . . . . . . . . . . 5-8 R22 Beta . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9 R22 Beta II . . . . . . . . . . . . . . . . . . . . . . . . . 5-10 Height-Velocity Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11 Noise Characteristics . . . . . . . . . . . . . . . . . . 5-12 INTENTIONALLY BLANK FAA APPROVED: 17 NOV 2021 5-1 ROBINSON R22 SERIES SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE GENERAL IGE hover controllability has been substantiated in 17 knot wind from any direction up to 9800 feet (2990 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. NOTE Hover performance data given is with carburetor heat off. Full carburetor heat reduces hover ceilings by up to 2000 feet (610 meters). Indicated airspeed (KIAS) shown on charts assumes zero instrument error. DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated to an outside air temperature of 38°C (100°F) at sea level or 23°C (41°F) above ISA at altitude. FAA APPROVED: 16 MARCH 1979 5-2 ROBINSON MODEL R22 SECTION 5 PERFORMANCE AIRSPEED CALIBRATION CURVE ROBINSON MODELR22 SECTIONS PERFORMANCE E-t r-1 ~141-+,,Ll-i,..,i:.1-~+-~i-~. la. 0 gl2~+-...,.:;.+-.,...:;.+-~;.+--i,,,==+,-4 ... >< r.1101-..:;....,._,;,a....-----...........-:'-i-~ •~-t~.--1--,,4 § E-t ~ 8~-l--.~4--,,~-1,-.,-t:;--4-~-!-.,jo:::~-- ----- ..:I < >- 6 1-,.-,:.....-1-,.4-+,.,4--1-,4-4-,1,4--1-~-+-.. ·_,.,.-'--I E-t...Ill ~ 4s::-+-,,,o<q._-4-,,<:+-..i,.o::+-,-..,...q......y,.q..-1-,,.q..-1-, Cl -2L..C.....___..\.L.._.._..........._...._...,_...._.....__.__.........,___.___.__.___. -40 -30 -20 -10 0 10 20 30 40 TEMPERATURE, DEGREES C I I I I I I J I I I I l I I I I I I I I I I I I I I I I j I I j I I I I I I I -40 -20 0 20 40 60 80 TEMPERATURE.DEGREES F DENSITY Al TITUDE CHART FAA APPROVED 16 MARCH 1979 I I I I 100 5-3 ROBINSON MODEL R22 I-'U, 0 0 ~ X "':i: w0 :::J >- .=_J < w a: :::J rJl rJl w a: 0. 14 13 12 11 10 9 8 7 6 5 4 3 2 1 0 900 SECTIONS PERFORMANCE IN GROUND EFFECT AT2 FOOT SKID CLEARANCE FULL THROTTLE AND 104% RPM GROSS WEIGHT· KGS. 425 450 475 500 525 550 575 . . I ·c OAT "' "F -20 - 4 • \: l". ~/' -10 + 14 0 + 32 , ~ I 0- .,__ +10 + 50 +20 + 68 ~ ~o c ,, +30 + 86 ~ '✓,"- +40 + 104 - / r-,... o,_, o"- "-.,.- STANDARD DAY ,,, ' ~✓~~ x✓o~· ~ -~ ~ \ x<"o DENSITY ALTITUDE. \"' Ko~~12,600 FT x""o,~ 1000 1200 GROSS WEIGHT· LBS. R22 STANDARD 0-320-A2B OR A2C ENGINE ' ~ ~ ~ ~ ' 1300 IGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 15 SEPTEMBER 1987 5.4 t- u. 0 0 0 ~ X w Cl ROBINSON MODEL R22 SECTION 5 PERFORMANCE IN GROUND EFFECT AT 2 FOOT SKID CLEARANCE FULL THROTTLE 104% RPM ZERO WIND GROSS WEIGHT - KG 425 450 475 500 525 550 575 14 ,..---L...---'r---+----,'----r"----.-'----.--L.--, 12 9 OAT -20 - 4 - 10 + 14 0 + 32 + 10 + 50 +20 + 68 +30 + 86 +40 + 104 ~ 8 DENSITY ALTITUDE 12,600 FT i= ....J <I: w 7 a: :::) en m 6 a: a. 5 4 3 2 MAX GROSS WEIGHT ~-,.__--+---+----t--+---+---+---t'--- R22 ALPHA + ~-,.__--+----+----1--+---+---+---1---+-BETA- 900 1000 1100 1200 GROSS WEIGHT - LB R22 HP, ALPHA, & BETA O-320-B2C ENGINE 1300 1400 I IGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 13 OCT 2000 5-5 ROBINSON MODEL R22 SECTION 5 PERFORMANCE I- u. 0 0 0 ~ >( 0. :c w 0 ::J I- j:: ....J ~ w a: ::J (/) (/) w a: a.. 14 13 12 11 10 9 8 7 6 5 IN GROUND EFFECT AT 2 FOOT SKID CLEARANCE FULL THROTTLE 500 1100 103-104% RPM ZERO WIND GROSS WEIGHT - KG 550 STANDARD DAY 1200 1300 GROSS WEIGHT - LB R22 BETA II 0-360-J2A ENGINE 600 IGE HOVER CEILING VS. GROSS WEIGHT 650 1400 *Hover controllability with 17 knot wind substantiated up to 9800 feet density altitude. FAA APPROVED: 13 OCT 2000 5-6 ROBINSON MODEL R22 SECTION 5 PERFORMANCE OUT OF GROUND EFFECT, ZERO WIND LIMIT MANIFOLD PRESSURE TO CRITICAL ALTITUDE FULL THROTTLE ABOVE CRITICAL ALTITUDE 104% RPM GROSS WEIGHT - KG 425 450 475 500 525 550 575 14 r----'-...---"T----'r----f,---,-4---.......-..,.........._-, OAT t- u.. 0 ·c -20 -10 0 + 10 +20 --;-----1--t-- +30 STANDARD DAY +40 8 9 1---+----,4-4-~=---~~~--i--+--~ ~ X r."" LU 0 ::> t-- 5<l: 7 DENSITY ALT ITU DE -t-----"'tt""'.,_....."c't-"'c-'\oc+~---"llc------1 12,600 FT LU 61---+----+---+---+---'r-l,.....__.._._,_.,..+-__ er: ::> (/) ~ 51---+---+---+---+----t---------,+->..a..,-- cr: a.. 2 t---+---+---+---+----t--+---+---11 1 t---+---+---+---+----t--+---+---1 0 ________.__......._____..___......._ _, 900 1000 1100 1200 GROSS WEIGHT - LB R22 STANDARD O-320-A2B OR A2C ENGINE OGE HOVER CEILING VS. GROSS WEIGHT 1300 "F - 4 + 14 + 32 + 50 + 68 + 86 + 104 FAA APPROVED: 13 OCT 2000 5-7 I- ROBINSON MODEL R22 SECTION 5 PERFORMANCE OUT OF GROUND EFFECT, ZERO WIND LIMIT MANIFOLD PRESSURE TO CRITICAL ALTITUDE FULL THROTTLE ABOVE CRITICAL ALTITUDE 104% RPM GROSS WEIGHT - KG 425 450 475 500 525 550 575 600 625 14 _ .......,....-..__ _,,__ _..__,..,__.,....___..________....... OAT •F -20 - 4 -10 + 14 12 ..--;----;-'""r""l~~---t-- STANDARD DAY - 0 + 32 + 10 + 50 +20 + 68 +30 + 86 +40 + 104 HP MAXIMUM GROSS ~ 9-----------.-.....-...-._..,. WEIGHT 0 0 0 1: a---------------__,~ ~ 7 ::> 1- DENSITY ALTITUDE 12,600 FT 5 61---1----+---+--+---1--~ <t: w a: 1300 lbs. ALPHA MAXIMUM GROSS WEIGHT 1370 lbs. ~ 5t--+---+---+--+---l--+---+-~~~,-++--+-i Cf> u,i 1---------------------0 __.,,__ _,_____._ ___.__.,.__ _,_____...,.....,._ 900 1000 1100 1200 GROSS WEIGHT LB R22 HP & ALPHA O-320-82C ENGINE 1300 OGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 13 OCT 2000 1400 5-8 I- u. 0 0 0 ~ )( Io. w Cl :, I- j::: ....J <( w a: :, V) V) w a: a. ROBINSON MODEL R22 SECTION 5 PERFORMANCE OUT OF GROUND EFFECT, ZERO WIND TAKEOFF POWER OR FULL THROTTLE 104% RPM GROSS WEIGHT - KG 425 450 475 500 525 550 575 600 625 14 13 12 11 10 9 8 7 6 5 4 3 2 1 0 900 . . . " OAT oc Of -20 - 4 '~ ~ v-STANDARD DAY- -10 + 14 ~ ~ 0 + 32 +10 + 50 \ ' +20 + 68 +30 + 86 / ~ ~ '~ +40 + 104 '~ ~~o ~ MAXIMUM ~ ~'.lo'- 0 '- ~ ~".lo" ?o"'-. DENSITY ALTITUDE '-""'o" "110'\.. 12,600 FT 1000 " 1100 1200 GROSS WEIGHT - LB R22 BETA 0-320-82C ENGINE GROSS " WEIGHT I 0 I ~ I ~ ~ J ~ ~ I ~ "\, ~ "l \1 "' "'I'\ ' 1300 1400 OGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 23 FEB 2004 5-9 ROBINSON MODEL R22 SECTION 5 PERFORMANCE f- LL 0 0 0 ~ X Io. w 0 :::, f- i=_J <i: w a: :::, [f) [f) w a: c.. 14 13 12 11 10 9 8 7 6 5 4 3 2 OUT OF GROUND EFFECT, ZERO WIND TAKEOFF POWER OR FULL THROTTLE 104% RPM GROSS WEIGHT - KG 475 500 525 550 575 600 625 650 STANDARD DAY MAXIMUM l' GROSS 'c-'- WEIGHT I OAT oc OF -20 - 4 -10 + 14 0 + 32 +10 + 50 +20 + 68 +30 + 86 +40 + 104 0 ,___...__.....____________________ 1000 1200 1300 R22 BETA II O-360-J2A ENGINE 1400 OGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 23 FEB 2004 5-10 FAA APPROVED: 23 FEB 2004 5-11 ROBINSON R22 SERIES SECTION 5 PERFORMANCE FAA APPROVED: 22 FEB 2024 5-12 ROBINSON R22 SERIES SECTION 5 PERFORMANCE NOISE CHARACTERISTICS The following noise level complies with 14 CFR Part 36, Appendix J and ICAO Annex 16, Chapter 11 noise requirements for later versions with the horizontal stabilizer mounted under the tailcone forward of the tail rotor. The noise level was obtained from FAA-approved noise test data. Models: R22 R22 Alpha & Beta Engine: Lycoming 0-320-A2B, 0-320-A2C, & 0-320-B2C Lycoming 0-320-B2C & 0-360-J2A Gross Weight: 1300 lbs (590 kg) 1370 lbs (622 kg) Vh: 95 KTAS The flyover sound exposure level (SEL) is 77.4 dB(A). This noise level meets 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 level of this aircraft is or should be acceptable or unacceptable for operation at, into, or out of any airport. SECTION 6 WEIGHT AND BALANCE CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1 Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . 6-2 Loading Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4 REVISED: 21 FEB 2014 6-i ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE INTENTIONALLY BLANK SECTION 6 WEIGHT AND BALANCE GENERAL The helicopter must be flown only within weight and balance limits specified in Section 2. Loadings outside these limits can result in insufficient control travel for safe operation. The center of gravity may be adjusted by adding removable ballast (any appropriate item of mass) to an under-seat baggage compartment. Recalculate weight and balance after adding ballast, and verify ballast meets baggage compartment limits given in Section 2. Loaded helicopter weight and balance can be determined using the method given under LOADING INSTRUCTIONS. In accordance with FAA procedures, the detail weight and balance data of this section are not subject to FAA approval. The loading instructions of this section, however, have been approved by the FAA as satisfying all requirements for instructions on loading of the rotorcraft within approved limits of weight and center of gravity and on maintaining the loading within such limits. CAUTION Fuel burn causes CG to move forward during flight. Always determine safe loading with empty fuel as well as with takeoff fuel. Payload may be limited by forward CG as fuel is burned. ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-1 WEIGHT AND BALANCE RECORD The following form should be used to maintain a continuous record of your helicopter’s weight and balance. Each time an item of equipment is removed or installed, an entry must be made and the new empty CG determined. The original factory weight and balance and an equipment list is supplied with each helicopter on a form which is inserted at the end of this section. This weight and balance provides the first entry in the Weight and Balance Record form. NOTE Calculated CG with full fuel and 135 lb pilot (130 lb pilot without auxiliary fuel tank) must be within CG limits. Following modification, adjustment to fixed nose ballast may be required. See R22 Maintenance Manual. REVISED: 21 FEB 2014 6-2 ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 21 FEB 2014 6-3 WEIGHT AND BALANCE RECORD (Continuous History of Changes in Structure or Equipment Affecting Weight and Balance) HELICOPTER MODEL R22 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 R22 SERIES SECTION 6 WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD (cont’d) REVISED: 22 FEB 2024 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 and baggage under right seat 78.0* +10.7 Passenger and baggage under left seat 78.0* —9.3 Main fuel** 108.6 —11.0 Aux fuel** 103.8 +11.2 Doors 5.2 each 77.5 ±21.0 Removable controls (cyclic, collective, pedals) 2.6 66.3 —12.9 Items on accessory mount bars 53.0 ±12.0 * Use 79.0 in. for aircraft prior to S/N 0256 with early-style seats. If additional backrest cushion is used, subtract thickness of compressed cushion. ** A longitudinal arm of 106.9 in. may be used for combined main and aux fuel. ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 22 FEB 2024 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 R22 SERIES SECTION 6 WEIGHT AND BALANCE 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 880 104.0 —0.1 91,520 —88 Remove right door —5.2 77.5 21.0 —403 —109 Remove left door 77.5 —21.0 Remove left seat controls 66.3 —12.9 Right seat pilot and baggage 170 78.0 10.7 13,260 1819 Left seat passenger and baggage 160 78.0 —9.3 12,480 —1488 Items on accessory mount bars 5 53.0 12.0 265 60 Zero usable fuel weight and CG* 1209.8 96.8 0.2 117,122 194 Usable main fuel at 6 lb/gal. 101.4 108.6 —11.0 11,012 —1115 Usable aux fuel at 6 lb/gal. 56.4 103.8 11.2 5854 632 Takeoff Gross Weight and CG* 1367.6 98.0 —0.2 133,988 —289 * CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 22 FEB 2024 6-6 ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 22 FEB 2024 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 right door 77.5 21.0 Remove left door 77.5 —21.0 Remove left seat controls 66.3 —12.9 Right seat pilot and baggage 78.0 10.7 Left seat passenger and baggage 78.0 —9.3 Items on accessory mount bar 53.0 ±12.0 Zero usable fuel weight and CG* Usable main fuel at 6 lb/gal. 108.6** —11.0 Usable aux fuel at 6 lb/gal. 103.8** 11.2 Takeoff Gross Weight and CG* * CG location (arm) for loaded helicopter is determined by dividing total moment by total weight. ** A longitudinal arm of 106.9 in. may be used for combined main and aux fuel. Do not use combined main and aux fuel if calculating lateral arm. INTENTIONALLY BLANK ROBINSON R22 SERIES SECTION 6 WEIGHT AND BALANCE REVISED: 23 FEB 2004 6-8 REVISED: 17 NOV 2021 7-i ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION SECTION 7 SYSTEMS DESCRIPTION CONTENTS Page General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-1 Rotor Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-2 Drive System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Powerplant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-3 Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-4 Removable Flight Controls . . . . . . . . . . . . . . . . . . . . . . . 7-5 RPM Governor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-6 Control Trim and Friction . . . . . . . . . . . . . . . . . . . . . . . . 7-7 Engine Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-8 Clutch Actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-9 Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-10 Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-11 Lighting System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-17 Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18 Optional Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-18 Audio System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-22 Pitot-Static System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Dual Tachometer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-23 Warning and Caution Lights . . . . . . . . . . . . . . . . . . . . . . 7-24 Audio Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-24 Engine Monitoring Unit . . . . . . . . . . . . . . . . . . . . . . . . . 7-25 Cabin Heating and Ventilation . . . . . . . . . . . . . . . . . . . . 7-26 Seats, Belts, and Baggage . . . . . . . . . . . . . . . . . . . . . . . 7-27 Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-27 Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-28 Engine Primer System (Optional) . . . . . . . . . . . . . . . . . . 7-28 Carbon Monoxide Detector . . . . . . . . . . . . . . . . . . . . . . 7-29 ADS-B Equipment . . . . . . . . . . . . . . . . . . . . . 7-30 Emergency Locator Transmitter (Optional) . . . . . . . . . . . 7-31 Accessory Mounts (Optional) . . . . . . . . . . . . . . . . . . . . 7-32 Cockpit Camera (Optional) . . . . . . . . . . . . . . . . . . . 7-33 INTENTIONALLY BLANK REVISED: 5 MAR 2015 7-1 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION SECTION 7 SYSTEMS DESCRIPTION GENERAL The R22 is a two-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 primary loads. Fiberglass and thermoplastics are used in the secondary cabin structure, engine cooling shrouds, and various other ducts and fairings. The cabin doors are also constructed of fiberglass and thermoplastics. A right-side cowl door provides access to the main gearbox and drive system. Additional access to controls and other components for maintenance is provided by removable panels and cowlings. Stainless steel firewalls are located forward of and above the engine. Both cabin doors are removable. Refer to Section 8 for removal and installation procedures. REVISED: 21 FEB 2014 7-2 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION 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 stopping or starting. Pitch change bearings for each blade are enclosed in a housing at the blade root. The housing is filled with oil and sealed with an elastomeric boot. Each blade has a thick stainless steel spar at the leading edge which is resistant to corrosion and erosion. The skins are bonded to the spar approximately one inch aft of the leading edge. Blades must be refinished if the paint erodes to bare metal at the skin-to-spar bond line. Bond may be damaged if bond line is exposed. The tail rotor has two all-metal blades and a teetering hub with a fixed coning angle. The pitch change bearings have self-lubricated liners. The teeter hinge bearings are elastomeric or have self-lubricated liners. The tail rotor blades are constructed with aluminum skins and root fittings. Maintaining the paint finish will reduce corrosion and erosion. REVISED: 21 FEB 2014 7-3 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION DRIVE SYSTEM A vee-belt sheave is bolted directly to the engine output shaft. Vee-belts transmit power to the upper sheave which has an overrunning clutch contained in its hub. The inner shaft of the clutch transmits power forward to the main rotor and aft to the tail rotor. Flexible couplings are located at the main gearbox input and at each end of the long tail rotor drive shaft. The main gearbox contains a single-stage spiral-bevel gear set which is splash lubricated. A cooling duct under the box is connected to the top of the engine shroud. The main gearbox is supported by four rubber mounts. The long tail rotor drive shaft has no support bearings but has a lightly-loaded damper bearing. The tail gearbox contains a single 90º splash-lubricated spiral-bevel gear set. POWERPLANT One Lycoming four-cylinder, horizontally-opposed, over- head-valve, air-cooled, carbureted engine with a wet sump oil system powers the helicopter. The engine is equipped with a starter, alternator, shielded ignition, two magnetos, muffler, oil cooler, and induction air filter. See Sections 1 and 2 for powerplant specifications and limitations. A direct-drive, squirrel-cage fan mounted to the engine output shaft supplies cooling air to the cylinders and oil cooler via a fiberglass and aluminum shroud. Induction air enters through an inlet on the right side of the fuselage and passes through a flexible duct to the carburetor air box. A hot air scoop supplies heated air to the air box. A sliding valve controlled by the pilot allows either cool or warm air to flow into the box, through the air filter, and up into the carburetor. The pilot should read and adhere to procedures recom- mended in the Lycoming Operator’s Manual to obtain max- imum engine life and efficiency. REVISED: 21 FEB 2014 7-4 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION FLIGHT CONTROLS Dual controls are standard equipment and all primary controls are actuated through push-pull tubes and bellcranks. Bearings used throughout the control system are either sealed ball bearings which do not require lubrication or have self-lubricated liners. Flight control operation is conventional. The cyclic is center mounted with the left and right control grips mounted to a cross tube which pivots on the center cyclic post. On later aircraft, the pilot’s cyclic grip angle can be adjusted fore and aft relative to the cross tube by a mechanic to achieve the most comfortable hand position. The most forward position provides the most control clearance at aft cyclic for larger pilots. Pilots should always verify the ability to apply full control travel prior to flight. Collective operation is conventional. The engine throttle is correlated to collective inputs through a mechanical linkage. When the collective is raised, the throttle is opened and when the collective is lowered, the throttle is closed. The collective stick also incorporates a twist grip throttle control which is described in the Engine Controls section. CAUTION Above 4000 feet, throttle-collective correla- tion and governor are less effective. There- fore, power changes should be slow and smooth. CAUTION At high power settings above 4000 feet, the throttle is frequently wide open and RPM must be controlled with collective. REVISED: 21 FEB 2014 7-5 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION 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. 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 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. REVISED: 21 FEB 2014 7-6 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION RPM GOVERNOR The governor maintains engine RPM by sensing changes and applying corrective throttle inputs through a friction clutch which can be easily overridden by the pilot. The governor is active only above 80% engine RPM and can be switched on or off using the toggle switch on the end of the right seat collective. The governor is designed to assist in controlling RPM under normal conditions. It may not prevent over- or under-speed conditions generated by aggressive flight maneuvers. CAUTION When operating at high density altitudes, governor response rate may be too slow to prevent overspeed during gusts, pull-ups, or when lowering collective. REVISED: 26 OCT 2016 7-7 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION CONTROL TRIM AND FRICTION Balancing trim springs are incorporated in the cyclic and collective controls. The collective-up spring balances the rotor loads, allowing the pilot to remove his left hand from the collective during most flight regimes. The longitudinal cyclic has a fixed bungee spring which cancels most longitudinal stick forces during cruise flight. The lateral cyclic is equipped with an on-off trim spring to cancel the left stick force which occurs during high speed flight. The spring is actuated by a push-pull knob located just forward of the cyclic stick. For S/N 550 and subsequent, fine adjustment of the trim force is controlled by the knob located on the left side of the console. CAUTION If mixture control is inadvertently pulled in flight, engine stoppage will result. To avoid pulling wrong control, always reach around left side of cyclic center post to actuate lateral trim. 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 stick. It is actuated aft to increase friction and forward to release it. The cyclic friction knob is located left of the cyclic center post. Turning the knob clockwise applies friction to both longitudinal and lateral cyclic. CAUTION Control friction must be used with caution during flight. Excessive friction may make the helicopter difficult to control. The pedals actuate push-pull controls connected directly to the tail rotor pitch control and do not incorporate any trim spring or friction devices. REVISED: 21 FEB 2014 7-8 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION ENGINE CONTROLS A twist-grip throttle control is located on each collective stick. The controls are interconnected and actuate the throttle valve through a mechanical linkage. The engine throttle is also correlated to collective inputs through a mechanical linkage. When the collective is raised, the throttle is opened and when the collective is lowered, the throttle is closed. The electronic engine governor makes minor throttle adjustments by rotating the twist grip to maintain RPM within power-on limits. Manual manipulation of the twist grip is not typically required except during start up, shut down, autorotation practice, and emergencies. An overtravel spring located in the throttle linkage allows the pilot to roll throttle off beyond the idle stop prior to a ground contact (run-on) autorotation landing. This prevents the throttle from opening when the collective is raised. Correct throttle linkage adjustment may be verified during preflight by rolling the twist-grip through the overtravel spring and holding against the hard idle stop. The carburetor throttle arm should just barely start to move when the collective is raised full up. Other engine controls include a mixture control located forward and to the right of the cyclic center post and a carburetor heat control located to the right and aft of the cyclic. R22s with O-360 engines are equipped with Carb Heat Assist which is described in Section 4. CAUTION In-flight leaning with mixture control is not recommended. If mixture is leaned on the ground at high altitude, be sure it is pushed back in before descending to lower altitude. Otherwise, engine may quit. NOTE On some aircraft, the mixture control is located on the console face. The mixture guard is not used with this mixture control. REVISED: 26 OCT 2016 7-9 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION CLUTCH ACTUATOR After the engine is started, it is coupled to the rotor drive system through vee-belts which are tensioned by raising the upper drive sheave. An electric actuator, located between the drive sheaves, raises the upper sheave when the pilot engages the clutch switch. The actuator senses compressive load (belt tension) and switches off when the vee-belts are properly tensioned. The clutch caution light illuminates whenever the actuator circuit is energized, either engaging, disengaging, or retensioning the belts. The light stays on until the belts are properly tensioned or completely disengaged. Belt slack during engine start should be adjusted such that blades begin turning within five seconds of clutch engagement. Excessive slack may cause belts to jump out of sheave grooves during start. Periodic readjustment by a mechanic may be required as belts wear in service. A fuse located on or near the test switch panel prevents an actuator motor overload from tripping the circuit breaker. If the fuse blows, the actuator motor will stop but the clutch caution light will remain illuminated. An open circuit breaker removes power from both the motor and the light. With an open circuit breaker, no belt tensioning will occur, and the light will not function to indicate an abnormal condition. CAUTION Never take off while clutch caution light is on. REVISED: 26 OCT 2016 7-10 ROBINSON R22 SERIES SECTION 7 SYSTEMS DESCRIPTION FUEL SYSTEM The fuel system is gravity-flow (no fuel pumps) and includes a main tank, an optional auxiliary tank, a shutoff valve control located behind the left seat, and a strainer (gascolator). Fuel tanks on later aircraft have flexible bladders in aluminum enclosures while earlier aircraft use all-aluminum tanks. Fuel tank air vents are located inside the mast fairing. Plunger-style drain valves are provided for the gascolator and for each fuel tank sump. The gascolator is located on the lower left side of the firewall. The drain valves for the auxiliary tank and bladder-style main tank are located inside the cowl door below the auxiliary tank. Plastic tubes attached to the valves allow fuel to be drained overboard. Fuel samples are taken by pushing on the plunger(s). For all-aluminum main tanks, the drain is located on the left side of the fuselage and is opened by pushing in on the plastic tube. On newer heli