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CLASS - Robinson R44

CLASS QSUBSCRIPTION SERVICEIf you wish to receive future changes to the r44 pilot s operating handbook and copies of future Safety Notices, you may order online at The CLASS Q subscription costs $40 USD for a period of two may also remit your payment by filling out the contact information below and sending it and your check or money order to: Robinson HELICOPTER COMPANY2901 Airport DriveTorrance, CA 90505 Note: The date stamped below reflects the revision of this handbook at the time it was assembled. Please refer to for date of most recent revision. If outdated, the most recent revision is available for an additional charge of $20 :Complete Address:Phone:E-mail:Aircraft Serial Number:INTENTIONALLY BLANKROBINSON MODEL R44 LOG OF PAGESLOG OF PAGES APPROVED BY FAATYPE CERTIFICATE NO. H11 NMiiCoverLog of PagesSection 2 LimitationsSection 3 EmergencyProceduresSection 4 NormalProceduresSection 5 PerformanceSection Dec 9211 May 202-i2-12-22-32-42-52-616 Apr 0321 Oct 167 May 1921 Feb 1421 Feb 1417 Dec 197 May 183-i3-13-23-33-43-511 May 2021 Oct 1621 Feb 1421 Feb 1421 Feb 1417 Dec 194-i4-14-24-34-44-54-64-721 Oct 167 May 187 May 187 May 187 May 187 May 1811 May 2011 May 205-i5-15-25-35-410 Dec 921 Sep 0417 Jun 9310 Dec 921

If you wish to receive future changes to the R44 Pilots Operating Handbook and copies of future Safety Notices, you may order online at www.robinsonheli.com. The Class Q subscription costs $40 USD for a period of two years. You may also remit your payment by filling out the contact information below and sending it and your check or money ...

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Transcription of CLASS - Robinson R44

1 CLASS QSUBSCRIPTION SERVICEIf you wish to receive future changes to the r44 pilot s operating handbook and copies of future Safety Notices, you may order online at The CLASS Q subscription costs $40 USD for a period of two may also remit your payment by filling out the contact information below and sending it and your check or money order to: Robinson HELICOPTER COMPANY2901 Airport DriveTorrance, CA 90505 Note: The date stamped below reflects the revision of this handbook at the time it was assembled. Please refer to for date of most recent revision. If outdated, the most recent revision is available for an additional charge of $20 :Complete Address:Phone:E-mail:Aircraft Serial Number:INTENTIONALLY BLANKROBINSON MODEL R44 LOG OF PAGESLOG OF PAGES APPROVED BY FAATYPE CERTIFICATE NO. H11 NMiiCoverLog of PagesSection 2 LimitationsSection 3 EmergencyProceduresSection 4 NormalProceduresSection 5 PerformanceSection Dec 9211 May 202-i2-12-22-32-42-52-616 Apr 0321 Oct 167 May 1921 Feb 1421 Feb 1417 Dec 197 May 183-i3-13-23-33-43-511 May 2021 Oct 1621 Feb 1421 Feb 1421 Feb 1417 Dec 194-i4-14-24-34-44-54-64-721 Oct 167 May 187 May 187 May 187 May 187 May 1811 May 2011 May 205-i5-15-25-35-410 Dec 921 Sep 0417 Jun 9310 Dec 9216 Aug 019-i17 Dec May 187 May 1817 Dec 197 May 1821 Oct 1621 Feb 143-63-73-83-93-103-1121 Oct 1617 Dec 195 Nov 9921 Oct 1611 May 2011 May 204-84-94-104-114-124-134-144-1510 Jul 1221 Oct 167 May 1910 Jul 1210 Jul 1221 Oct 1611 May 2013 May 095-55-65-75-816 Aug 0110 Dec 9218 Dec 1517 Jun 93 Approved By:Manager, Flight Test Section, AIR-716 Federal Aviation AdministrationLos Angeles, CADate of Approval.

2 11 MAY 2020 Robinson MODEL R44 LOG OF PAGESREVISED: 11 MAY 2020iiiLOG OF PAGES NOT REQUIRING FAA APPROVALS ection 1 GeneralSection 6 Weight andBalanceSection 7 SystemsDescriptionSection 8 Handling andMaintenanceSection 10 Safety Jul 1210 Jul 1210 Jul 1216 Apr 0311 May 206-i6-16-26-36-421 Feb 1421 Feb 1421 Feb 1421 Feb 1421 Feb 147-i7-17-27-37-47-57-67-77-87-97-107-11 7-127-137-147-1511 May 2010 Mar 1510 Mar 1516 Apr 0321 Feb 1421 Feb 1421 Oct 167 May 1821 Oct 1621 Oct 1621 Oct 1621 Oct 1621 Feb 1421 Feb 1421 Feb 1421 Oct 168-i8-18-28-38-48-58-68-77 May 197 May 197 May 1917 Dec 197 May 197 May 197 May 197 May 1910-i10-110-210-321 Oct 165 Oct 1121 Oct 165 Oct Apr 0321 Oct 165 Oct 1121 Oct 166-56-66-76-821 Feb 1421 Feb 1421 Feb 14 21 Feb 147-167-177-187-197-207-217-227-237-247- 257-267-277-287-297-307-3121 Oct 167 May 1921 Feb 1421 Feb 1410 Mar 157 May 1921 Oct 1611 May 2011 May 2011 May 2011 May

3 2011 May 2011 May 2011 May 2011 May 2011 May 208-88-98-108-118-128-138-147 May 1911 May 2011 May 207 May 197 May 197 May 197 May 1910-410-510-621 Oct 167 May 187 May 18 Robinson MODEL R44 SECTION 1 GENERALREVISED: 16 APR 20031-3 THREE-VIEW OF R44 HELICOPTERROBINSON MODEL R44 SECTION 1 GENERALREVISED: 11 MAY 20201-4 DESCRIPTIVE DATAMAIN ROTORA rticulation Free to teeter and cone, rigid inplaneNumber of Blades 2 Diameter 33 feetBlade Chord inches inboard, inches outboardBlade Twist -6 DegreesTip Speed at 102% RPM 705 feet per secondTAIL ROTORA rticulation Free to teeter,rigid inplaneNumber of Blades 2 Diameter 58 inchesBlade Chord inches (constant)Blade Twist 0 Precone Angle 1 DegreeTip Speed at 102% RPM 614 feet per secondDRIVE SYSTEME ngine to Upper Sheave: Four double Vee-belts :1 speed reducing ratioUpper Sheave to Drive Line: Sprag-type overrunning clutchDrive Line to Main Rotor: Spiral-bevel gears with 11:57 speed reducing ratioDrive Line to Tail Rotor: Spiral-bevel gears with31:27 speed increasing ratioROBINSON MODEL R44 SECTION 1 GENERALREVISED: 16 APR 20031-5 DESCRIPTIVE DATA (cont d)POWERPLANTM odel: Lycoming 0-540-F1B5 Type: Six cylinder, horizontally opposed, direct drive, air cooled, carbureted, normally aspiratedDisplacement: cubic inchesNormal rating: 260 BHP @ 2800 RPMM aximum continuous rating in R44: 205 BHP at 2718 RPM (102% on tachometer)5 Minute takeoff rating in R44: 225 BHP at 2718 RPMC ooling system: Direct drive squirrel-cage blowerFUELA pproved fuel grades and capacity: See Section oil grades and capacity: See Section MODEL R44 SECTION 1 GENERALREVISED.

4 21 OCT 20161-6 PERFORMANCE DEFINITIONSKIASK nots Indicated Airspeed is speed shown on the airspeed Calibrated Airspeed is speed shown on the air-speed indicator corrected for instrument and position error. (See Section 5 for position error correction.)KTASK nots True Airspeed is airspeed relative to undisturbed air. It is KCAS corrected for pressure altitude and for best rate of level-flight speed at maximum continuous above mean sea level, indicated by the altimeter (corrected for instrument error) when the barometric subscale is set to the atmospheric pressure existing at sea indicated by the altimeter (corrected for instrument error) when the barometric subscale is set to inches of mercury ( mb).DensityAltitudeAltitude in ISA conditions at which the air would have the same density (it is pressure altitude corrected for OAT).

5 ISAI nternational Standard Atmosphere exists when pressure is inches of mercury at sea level, temperature is 15 C at sea level, and temperature decreases C per 1000 feet of Horsepower is actual power output of the Absolute Pressure is the absolute pressure in the engine intake Per Minute or speed of engine or rotor. (Shown by tachometer as percentage of 2665 engine RPM and 400 main rotor RPM).MCPM aximum Continuous Power (limited to 5 minutes in the R44).CriticalAltitudeAltitude at which full throttle produces maximum allowable power (MCP or TOP).TOGWT akeoff Gross MODEL R44 SECTION 1 GENERALREVISED: 5 OCT 20111-7 PERFORMANCE DEFINITIONS (cont d)OATO utside Air TemperatureCATC arburetor Air TemperatureCHTC ylinder Head TemperatureGPHG allons Per HourAGLA bove Ground LevelIGEIn Ground EffectOGEOut of Ground EffectALTA lternatorWEIGHT AND BALANCE DEFINITIONSR eferenceDatumA vertical plane from which horizontal distances are measured for balance purposes.

6 The longitudinal reference datum is 100 inches forward of the main rotor shaft centerline for the location along the helicopter fuselage given in terms of distance in inches from the longitudinal reference distance from a reference datum to the center of gravity (CG) of an weight of an item multiplied by its ofGravity (CG)Location on 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 LimitsExtreme CG locations within which the helicopter must be operated at a given FuelFuel available for flight FuelFuel remaining in the tank that cannot reliably provide uninterrupted fuel flow in the critical flight WeightWeight of a standard helicopter including unusable fuel, full operating fluids, and full engine EmptyWeightStandard empty weight plus weight of installed op-tional of occupants, cargo, and LoadDifference between maximum gross weight and basic empty MODEL R44 SECTION 1 GENERALREVISED: 21 OCT 20161-8 CONVERSION TABLESMETRIC TO ENGLISHM ultiplyByTo Obtaincentimeters (cm) (in)kilograms (kg) (lb) miles (mi) , (gal) (qt) (ft)millibars (mb) of mercury(in.)

7 Hg)ENGLISH TO METRICM ultiplyByTo Obtainfeet (ft) , (gal) (in) (cm)inches (in) (mm)inches of mercury(in. Hg) (mb)nautical (lb) (kg)quarts (qt) miles (mi) nautical mile = statute miles1 statute mile = nautical mileTEMPERATURE F = 9/5 ( C) + 32 C = 5/9 ( F 32) Robinson MODEL R44 SECTION 2 LIMITATIONSFAA APPROVED: 21 OCT 20162-1 SECTION 2 LIMITATIONSGENERALThis section includes operating limitations, instrument markings, and basic placards required for safe operation of the helicopter, its engine, and other standard systems. This helicopter is approved as a normal category rotorcraft under FAA Type Certificate No. H11NM as Model R44 in the serial number range 0002 to CODE FOR INSTRUMENT MARKINGSRedOperating limit. Edge of red line indicates limit. Pointer should not enter red during normal Cross-hatchPower-off or special operating procedure operating LIMITSNEVER-EXCEED AIRSPEED (Vne)2200 lb (998 kg) TOGW and below130 KIASOver 2200 lb (998 kg) TOGW120 KIASA utorotation100 KIASFor Vne reductions with altitude and temperature, see placard on page AIRSPEED LIMITS100 KIAS maximum at power above KIAS maximum with any combination of cabin doors MODEL R44 SECTION 2 LIMITATIONSFAA APPROVED: 7 MAY 20192-2 ROTOR SPEED LIMITSP ower OnMaximumMinimum*102% (408 RPM)101% (404 RPM)**Power OffMaximumMinimum108% (432 RPM)90% (360 RPM)*Transient operation at lower RPM permitted for emergency procedures training.

8 **99% (396 RPM) permitted on R44s with tachometers showing engine green arc from 99% to 102%.POWERPLANT LIMITATIONSENGINEOne Lycoming Model O-540-F1B5 operating LIMITSE ngine SpeedMaximum continuous 102% (2718 RPM)Maximum transient** 105% (2800 RPM)Cylinder Head Max Temperature 500 F (260 C)Oil Maximum Temperature 245 F (118 C)Oil PressureMinimum during idle25 psiMinimum during flight55 psiMaximum during flight 95 psiMaximum during start & warm up115 psiOil Quantity, minimum for takeoff 7 qt ( liters)Manifold Pressure: See placard on page 2-9 for MAP schedule.**Intentional operation above maximum continuous speed APPROVED: 21 FEB 20142-3 ROBINSONMODEL R44 SECTION 2 LIMITATIONSWEIGHT LIMITSM aximum gross weight2400 lb (1089 kg)Minimum gross weight1550 lb (703 kg)Maximum per seatincluding baggage compartment300 lb (136 kg)Maximum in any baggagecompartment50 lb (23 kg)CENTER OF GRAVITY (CG) LIMITSSee figure on page 2-4.

9 Reference datum is 100 inches forward of main rotor shaft all doors installed, a solo pilot weight of 150 lb (68 kg) or greater will ensure CG within limits. For lower pilot weight, compute weight and balance; removable ballast may be required to obtain CG at or forward of aft limit. (See Loading Instructions in Section 6.)FAA APPROVED: 21 FEB 20142-4 ROBINSONMODEL R44 SECTION 2 LIMITATIONSCENTER OF GRAVITY LIMITSROBINSON MODEL R44 SECTION 2 LIMITATIONSFAA APPROVED: 17 DEC 20192-5 FLIGHT AND MANEUVER LIMITATIONSA erobatic flight control inputs may produce high fatigue stresses and cause catastrophic failure of a critical cyclic pushovers 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.

10 To eliminate a low-G condition, immediately apply gentle aft cyclic. Should a right roll commence during a low-G condition, apply gentle aft cyclic to reload rotor before applying lateral cyclic to stop prohibited with governor selected off, with exceptions for in-flight system malfunction or emergency procedures in known icing conditions operating density altitude 14,000 operating altitude 9000 feet AGL to allow landing within 5 minutes in case of , RPM governor, low rotor RPM warning system, OAT gage, and cyclic trim or hydraulic control system must be operational for crew is one pilot in the right front seat. A flight instructor may act as pilot in command from the left front seat. Solo flight from right seat left seat belt must be up to 100 KIAS approved with any combination of cabin doors removed.


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