ROBINSON R22 SERIES SECTION 9 SUPPLEMENTS

nut self-locking torque). FAA APPROVED: 04 NOVEMBER 1994 9-3.5 ROBINSON MODEL R22 SECTION 9 POLICE VERSION SUPPLEMENT THIS PAGE INTENTIONALLY LEFT BLANK. FAA APPROVED: 04 NOVEMBER 1994 9-3.6 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 FAA APPROVED R22 PILOT'S OPERATING HANDBOOK SUPPLEMENT 4 R22 MARINER/MARINER II This supplement must be attached to the FAA Approved Robinson R22 Pilot's Operating Handbook when the helicopter is configured in the Mariner or Mariner II version. The information contained herein supplements or supersedes the basic manual only in those areas listed in this Supplement. For limitations, procedures, and performance information not contained in this Supplement, consult the basic R22 Pilot's Operating Handbook. FAA APPROVED chJ/%""""'1 Supervisor, Flight Test Section FAA, Western Aircraft Certification Office Northwest Mountain Region LOG OF REVISIONS Page Date Page No. No. 9-4.1 13 Oct 00 9-4.8 9-4.2 13 Oct 00 9-4.9 9-4.3 13 Oct 00 9-4.10 9-4.4 13 Oct 00 9-4.11 9-4.5 13 Oct 00 9-4-12 9-4.6 13 Oct 00 9-4.13 9-4.7 13 Oct 00 Date 13 Oct 00 13 Oct 00 13 Oct 00 13 Oct 00 13 Oct 00 13 Oct 00 REVISIONS ~~APPROVED BY ~ Manager, Flight ~N;, em. Federal Aviation Administration, LAACO Transport Airplane Directorate FAA APPROVED: 13 OCT 2000 9-4.1 ROBINSON MODEL R22 MARINER/MARINER II SECTION 1: GENERAL INTRODUCTION SECTION 9 SUPPLEMENT 4 This supplement contains the changes and additional data applicable for R22 Mariner and Mariner II helicopters. R22 Mariner/Mariner II helicopters are equipped with either float or standard landing gear, additional corrosion protection, and a modified horizontal stabilizer angle of incidence. Except as noted in this supplement, information in the basic manual pertaining to the R22 Beta is applicable to the R22 Mariner and information pertaining to the Beta II is applicable to the Mariner II. Float landing gear consists of inflated floats attached to the skid tubes, and skid extensions to support the aft portion of the float tubes. When float landing gear is installed, an additional stabilizer is installed at the bottom of the lower vertical stabilizer for improved controllability. Configuration changes between float and standard landing gear are permitted. SECTION 2: LIMITATIONS AIRSPEED LIMITATIONS NEVER EXCEED AIRSPEED (Vne) WITH FLOATS Power-On: 95 KIAS up to 3000 ft density altitude. Power-Off: 80 KIAS up to 7500 ft density altitude. Above these density altitudes, see placard on page 9-4.4. CENTER OF GRAVITY (CG) LIMITS See figure on page 9-4.3. Datum line is 100 inches forward of main rotor shaft centerline. KINDS OF OPERATION LIMITATIONS Only VFR day is approved when floats are installed. FAA APPROVED: 13 OCT 2000 9-4.2 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 2: LIMITATIONS (cont'd) WITH FLOATS 1400 a, 1 300 ...J ~ 1200 <D .... !il .,, 11 00 .,, 51<!l l 000 900 3 R 2 R ~ 1 R -2 L -3 L ----- WITHOUT FLOATS---- - FUSELAGE STATION (IN. FROM DATUM) 95 96 97 98 99 100 101 102 ~ 137~1 96.5 \ 121s-r \ \ 1125-)_ --I 1- I -I <r. I 95.5 101.5 MAIN ROTOR / ~~ / ~ r'-..... ,/ .:=.,:1.1R I ,_ L - ...I 0.8L- I ..,,-0.81- " V' " ,.,. V 2.2L "' II I I I I I I I I 242 244 246 248 250 252 254 256 258 260 FUSELAGE STATION (CM FROM DATUM) R22 MARINER/MARINER II CENTER OF GRAVITY LIMITS FAA APPROVED: 13 OCT 2000 650 600 ~ I 550 ,- :x: ::: 500~.,,.,, 51<!l 450 400 6 4 :E u 2 I <D 0 u _, -2 ~...... I- <_, -4 -6 9-4.3 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 2: LIMITATIONS (cont'd) PLACARDS In clear view of pilot: THIS ROTORCRAFT IS APPROVED FOR DAY AND NIGHT VFR OPERATIONS WITHOUT FLOATS INSTALLED OR DAY VFR OPERATIONS ONLY WITH FLOATS INSTALLED In clear view of pilot in flight: R22 Mariner NEVER EXCEED SPEED WITH FLOATS R22 Mariner II NEVER EXCEED SPEED WITHOUT FLOATS "o 2 10 Jlr• ■ aur• Alt. 1,000 , ..t NEVER EXCEED SPEED • KIAS WITH FLOATS NEVER EXCEED SPEED - KIAS WITHOUT FLOATS PRESS OAT· •c PRESS OAT· •c ALT-FT -20 -10 0 10 20 30 40 ALT-FT ·20 -10 0 SL SL - - 2000 95 94 91 88 -4000 94 90 86 83 79 2000 102 -4000 6000 90 86 82 78 74 69 6000 98 94 8000 86 82 77 72 67 62 57 8000 94 90 86 10000 77 72 66 61 56 51 10000 86 80 74 12000 66 60 55 NO FLIGHT 14000 54 12000 74 67 61 14000 61 ¥OR AUTOROTATION, USE 80 KIA$ ABOVE HEAVY LINE Located on floats: SEE PILOT'S HANDBOOK FOR PROPER INFLATION PRESSURE FAA APPROVED: 13 OCT 2000 10 20 30 99 98 94 91 90 87 82 80 75 69 68 62 57 NO FLIGHT 9-4.4 40 96 87 77 64 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 2: LIMITATIONS (cont'd) FLOAT PRESSURE LIMITS Minimum Float Pressure: 2 psig (psi gage) Maximum Float Pressure: 6 psig The following graph shows minimum float pressure required for a decrease in altitude or temperature. An increase in either altitude or temperature can be ignored as pressure relief valves will limit pressure to 6 psig. REQUIRED FLOAT PRESSURE VS. CHANGE IN ALTITUDE AND TEMPERATURE t:: 0 0 0 X a. :,: w C ::, ~ ·6 +--+---....,,__ ~ <I: ~ w <I) : -s+---+--+--+--~i-,....~"--4---"..!-->1 CAUTION Failure to maintain required pressure can result in inadequate buoyancy or in-flight instability. a: (.) w C 2 I MIN 4 5 INITIAL FLOAT PRESSURE · PSIG SAMPLE CALCULATION: Conditions at destination: Initial Conditions: Subtract to obtain expected 6 I MAX Pressure Altitude 1000 ft 5500 ft Temp 15•c 5•c change in altitude and temp: -4500 ft + 1o·c Using graph, locate -4500 ft line, read across to + 1o·c line, then down for minimum initial float pressure required, approximately 3. 7 psig. FAA APPROVED: 13 OCT 2000 9-4.5 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 3: EMERGENCY PROCEDURES GENERAL Without floats, emergency procedures in the basic manual apply. The following procedures are applicable when floats are installed. POWER FAILURE ABOVE 500 FEET AGL Autorotation to Land: Same as non-float R22. Autorotation to Water: Steps1 -7 same as non-float R22. 8. At about 8 feet AGL, apply forward cyclic to level helicopter and raise collective just before touchdown to cushion landing. Touchdown in slight nose high attitude with nose straight ahead. 9. Maintain cyclic in touchdown position and hold collective up until forward motion has stopped. See caution below. POWER FAILURE BETWEEN 8 AND 500 FEET AGL Autorotation to Land: Same as non-float R22. Autorotation to Water: Steps 1 -4 same as non-float R22. 5. At about 8 feet AGL, apply forward cyclic to level helicopter and raise collective just before touchdown to cushion landing. Touchdown in slight nose high attitude with nose straight ahead. 6. Maintain cyclic in touchdown position and hold collective up until forward motion has stopped. CAUTION Lowering collective or applying forward cyclic while helicopter is moving forward on water can cause floats to submerge and helicopter to nose over. DITCHING Not applicable when floats are installed. FAA APPROVED: 13 OCT 2000 9-4.6 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 4: NORMAL PROCEDURES DAILY OR PREFLIGHT CHECKS 14. Inflatable Floats Float Pressure ...... Check (See Section 2) Float Condition Check CAUTION Helicopters equipped with inflated floats have an adverse roll characteristic; when sideslipping nose left or right the helicopter will tend to roll in the opposite direction. To avoid adverse roll, keep helicopter trimmed with zero sideslip and exercise extreme caution when performing simulated power failures. OPERATION ON WATER Maximum recommended water taxi speed is 5 knots. Some application of collective is required. CAUTION If starting or stopping rotor on water, ensure area is clear as helicopter can rotate one complete turn while tail rotor RPM is low. CAUTION To avoid contacting rotor teeter stops, do not apply full cyclic control during water taxi. NOTE Safe operation on water has been demon- strated in waves up to 1 2 inches (trough to crest). FAA APPROVED: 13 OCT 2000 9-4.7 ROBINSON MODEL R22 MARINER/MARINER II SECTION 9 SUPPLEMENT 4 SECTION 4: NORMAL PROCEDURES (cont'd) PRACTICE AUTOROTATION - WITH GROUND CONTACT Same as non-float R22 except rear of floats may be scuffed on pavement during touchdown. Protective tape should be applied to bottom of floats and inspected for wear after touchdowns. PRACTICE AUTOROTATION - WITH WATER CONTACT Same as practice autorotation with ground contact in basic manual except touch down in slight nose high attitude with nose straight ahead. Maintain cyclic in touchdown position and collective up until forward motion has stopped. CAUTION Lowering collective or applying forward cyclic while helicopter is moving forward on water can cause floats to submerge and helicopter to nose over. SECTION 5: PERFORMANCE HOVER PERFORMANCE In-ground-effect OGE) and out-of-ground-effect (OGE) hover performance charts for the R22 Mariner are on pages 9-4.9 and 9-4.10. R22 Mariner II hover performance is equivalent to R22 Beta II hover performance. FAA APPROVED: 13 OCT 2000 9-4.8 ROBINSON SECTION 9 SUPPLEMENT 4 MODEL R22 MARINER/MARINER II I- LL 0 0 0 .... X C. I w 0 :::, I- i'.=...J <( w a.: :::, (/J (/J w a.: a. IN GROUND EFFECT AT 2 FOOT SKID CLEARANCE FULL THROTTLE AND 104% RPM 14 13 12 11 10 9 8 7 6 5 4 3 2 l 0 900 GROSS WEIGHT - KG 425 450 475 500 525 550 575 600 625 I OAT \~ ·c "F - \~ -20 - 4 STANDARD DAY 10 + 14 \~ ~A 0 + 32 - +10 + 50 + 20 + 68 ' +30 + 86 - \~ ~:' +40 + 104 \ '- I I /_' ~ ~ "':¾ I Yi "' ' ,~o >t._ MAX \ '\"' "- 1 " GROSS ~ ",. " WEIGHT ' ' l I , " '•' "' '- DENSITY ALTITUDE (12,600 ft) "- ;.,o ' ,,•vo I'-... ~ I"- " " " 1000 1100 1200 GROSS WEIGHT - LB R22 MARINER 0-320-B2C Engine "- 1300 IGE HOVER CEILING VS. GROSS WEIGHT '\ ~II I ~ ~I I'\ I I II I I 1400 FAA APPROVED: 13 OCT 2000 9-4.9 ROBINSON SECTION 9 SUPPLEMENT 4 MODEL R22 MARINER/MARINER II OUT OF GROUND EFFECT TAKEOFF POWER OR FULL THROTTLE AT 104% RPM 14 13 12 11 10 9 8 7 6 5 4 3 2 0 900 GROSS WEIGHT - KG 425 450 475 500 525 550 575 600 625 ' I I I ' ' ' I I \, \~ STANDARD DAY ~~ f\~~ ~ '~ "'~ ;¾ I \~" ~o," DENSITY ALTITUDE "" ""r"' " MAX (12,600 ft) GROSS ' .,,0 ... rs.. ~EirT "'·' ""'"'o ~ N "' "' ":--.. I ~ ~ I "' \ I I \ ,\ \\1' \I 1000 1100 1200 1300 1400 GROSS WEIGHT - LB R22 MARINER 0-320-B2C Engine 5 Minute Takeoff Rating OGE HOVER CEILING VS. GROSS WEIGHT FAA APPROVED: 13 OCT 2000 9-4.10 ROBINSON MODEL R22 MARINER/MARINER II SECTION 6: WEIGHT AND BALANCE CAUTION SECTION 9 SUPPLEMENT 4 When changing from float-equipped to non-float configuration or vice versa, weight and balance for basic helicopter must be revised and autorotation RPM readjusted per R22 Maintenance Manual. WEIGHT AND BALANCE RECORD Basic empty weight and CG in float and non-float configurations is included in the Weight and Balance Data provided with the helicopter. Modifications are to be recorded on page 6-5 of the basic manual. LOADING INSTRUCTIONS Determine loaded helicopter weights and moments per page 6- 7. These values must fall within the Weight and Moment envelope shown below. WITHOUT FLOATS WITH FLOATS ca _J I- I (.9 w ~ a: w I- c.. 0 u ::i w I 0 w 0 <( 0 _J ----- ---- 1300 !ZOO IIOO 1000 900 LOADED HELICOPTER MOMENT - 1000 inch-lbs. R22 MARINER/MARINER II Allowable CG Moment vs. Gross Weight Envelope REVISED: 13 OCT 2000 9-4.11 ROBINSON MODEL R22 MARINER/MARINER II SECTION 7: SYSTEMS DESCRIPTION SECTION 9 SUPPLEMENT 4 No change. SECTION 8: HANDLING, SERVICING AND MAINTENANCE GROUND HANDLING When floats are installed, special ground handling wheels are required. Refer to the R22 Maintenance Manual for wheel installation and removal procedures. FLOAT TUBES To promote long float tube life: 1. Do not inflate floats to a higher pressure than required in the Limitations section. 2. Do not arbitrarily inflate floats to the relief valve pressure. 3 Reduce pressure in floats if solar heating is causing an excessive pressure buildup. 4. Do not allow floats to sit uninflated for long periods of time, always maintain some pressure to keep shape when not in use. CAUTION When inflating chambers individually (without the use of a manifold), increase pressure in each chamber in 0.5 psig increments. REVISED: 13 OCT 2000 9-4.12 ROBINSON MODEL R22 MARINER/MARINER II SECTION 10: SAFETY TIPS SECTION 9 SUPPLEMENT 4 Flight characteristics and handling qualities of a helicopter with inflated floats are more critical than those for helicopters with conventional landing gear. For instance, helicopters with floats installed have an adverse roll characteristic, i.e. when sideslipping nose right or left, the helicopter will tend to roll in the opposite direction out of the turn. This could be extremely dangerous if a student or instructor failed to put in right pedal or put in the wrong pedal during a simulated power failure. Also, aerodynamic lift produced by the floats makes both RPM and longitudinal attitude control more difficult during autorotation entries. Helicopters with floats installed are also more gust sensitive and therefore more difficult to fly in turbulence. For these reasons, it is strongly recommended that floats be removed and standard gear installed when the helicopter is being used for primary flight instruction. When floats are installed, pilots must keep the helicopter trimmed with zero sideslip and exercise extreme caution when performing simulated power failures. REVISED: 13 OCT 2000 9-4.13 INTENTIONALLY BLANK FAA APPROVED R22 PILOT’S OPERATING HANDBOOK OPTIONAL AVIONICS SUPPLEMENT This supplement must be included in the FAA-approved Pilot’s Operating Handbook when certain factory-supplied optional avionics are installed. Information contained herein supplements or supersedes the basic manual only in those areas listed in this supplement. For limitations, procedures, and performance information not contained in this supplement, consult the basic Pilot’s Operating Handbook. APPROVED BY: Manager, West Flight Test Section, AIR-716 Federal Aviation Administration Los Angeles, CA DATE: 20 JUN 2019 Page 9-10.1 LOG OF PAGES * Manufacturer’s data, not FAA approved. ROBINSON R22 SERIES SECTION 9 OPTIONAL AVIONICS SUPPLEMENT Page No. Date 9-10.1 9-10.2* 9-10.3 20 JUN 19 20 JUN 19 20 JUN 19 Page No. Date 9-10.4* 9-10.5* 20 JUN 19 20 JUN 19 ISSUED: 20 JUN 2019 Page 9-10.2 SECTION 1: GENERAL INTRODUCTION This supplement provides additional information for certain avionics options. A set of manufacturers’ instructions for all installed avionics is provided with each new helicopter. The following equipment is addressed in this supplement: • Aspen Avionics EFD 1000H PFD NOTE For the Robinson Primary Flight Display (PFD) installation, the airspeed indicator, altimeter, compass, tachometer, and engine instruments are retained. Pilots should use the traditional instruments as primary unless fully familiar with the installed avionics. ROBINSON R22 SERIES SECTION 9 OPTIONAL AVIONICS SUPPLEMENT FAA APPROVED: 20 JUN 19 Page 9-10.3 SECTION 2: LIMITATIONS No change. SECTION 3: EMERGENCY PROCEDURES No change. SECTION 4: NORMAL PROCEDURES No change. SECTION 5: PERFORMANCE No change. SECTION 6: WEIGHT AND BALANCE No change. SECTION 7: SYSTEMS DESCRIPTION See below. SECTION 8: HANDLING AND MAINTENANCE No change. ROBINSON R22 SERIES SECTION 9 OPTIONAL AVIONICS SUPPLEMENT ISSUED: 20 JUN 19 Page 9-10.4 SECTION 7: SYSTEMS DESCRIPTION ASPEN EFD 1000H PFD The Aspen Electronic Flight Display (EFD) 1000H is a Primary Flight Display (PFD) optimized for helicopter use. It is available in a “Pilot” (basic) version or “Pro” (with more advanced navigation features) version. A typical instrument panel is illustrated on the following page. The manufacturer’s document for the EFD 1000H is: Title Document No. Aspen Avionics Evolution Flight Display EFD 1000H PFD Pilot’s Guide 091-00012-001 NOTE A Robinson part no. D327-4 light filter may be used to reduce reflections in the windshield at night. The light filter is installed by clipping it to the front of the display. Filter use is at pilot discretion. ROBINSON R22 SERIES SECTION 9 OPTIONAL AVIONICS SUPPLEMENT ISSUED: 20 JUN 19 Page 9-10.5 OPTIONAL INSTRUMENT PANEL WITH ASPEN EFD 1000H PFD (Exact panel configuration may vary with optional equipment and date of helicopter manufacture.) 1. VERTICAL SPEED INDICATOR 21. PILOT’S SIDE CONSOLE (OPT’L) 2. ENGINE AND ROTOR TACHS 22. ENGINE INSTRUMENTS 3. ALTIMETER 23. CARBURETOR AIR TEMP 4. MANIFOLD PRESSURE GAGE 24. CLOCK 5. PRIMARY FLIGHT DISPLAY 25. PANEL LIGHTS DIMMER 6. CLUTCH ACTUATOR SWITCH 26. NAVIGATION LIGHTS SWITCH 7. CLUTCH ACTUATOR LIGHT 27. ANTI-COLLISION LIGHT SWITCH 8. M.R. GEARBOX TEMP LIGHT 28. AVIONICS MASTER SWITCH 9. M.R. GEARBOX CHIP LIGHT 29. ALTERNATOR SWITCH 10. CARBON MONOXIDE LIGHT 30. BATTERY SWITCH 11. STARTER-ON LIGHT 31. CABIN AIR 12. T.R. GEARBOX CHIP LIGHT 32. INTERCOM 13. LOW FUEL LIGHT 33. OUTSIDE AIR TEMP/VOLTMETER 14. LOW RPM LIGHT 34. AVIONICS STACK 15. ALT LOW VOLTAGE LIGHT 35. CYCLIC RIGHT TRIM 16. OIL PRESSURE LIGHT 36. CYCLIC FRICTION 17. GOVERNOR-OFF LIGHT 37. ELT SWITCH (OPT’L) 18. FULL THROTTLE LIGHT 38. MIXTURE CONTROL 19. ROTOR BRAKE LIGHT 39. CARBURETOR HEAT 20. IGNITION SWITCH SECTION 7: SYSTEMS DESCRIPTION (cont’d) ROBINSON R22 SERIES SECTION 9 OPTIONAL AVIONICS SUPPLEMENT INTENTIONALLY BLANK