BONANZA G36 Specifi Cation And Description
BONANZA G36 Specification and DescriptionE-4063 THRU E-4080
ContentsTHIS DOCUMENT IS PUBLISHED FOR THE PURPOSEOF PROVIDING GENERAL INFORMATION FOR THEEVALUATION OF THE DESIGN, PERFORMANCEAND EQUIPMENT OF THE BONANZA G36. IT IS NOT ACONTRACTUAL AGREEMENT UNLESS APPENDEDTO AN AIRCRAFT PURCHASE AGREEMENT.1. GENERAL DESCRIPTION .22. GENERAL ARRANGEMENT.33. DESIGN WEIGHTS AND CAPACITIES .44. PERFORMANCE .45. STRUCTURAL DESIGN CRITERIA .46. FUSELAGE .47. WING.58. EMPENNAGE .59. LANDING GEAR .510. POWERPLANT .511. PROPELLER .612. SYSTEMS .613. FLIGHT COMPARTMENT AND AVIONICS .714. INTERIOR .1215. EXTERIOR .1216. ADDITIONAL EQUIPMENT.1217. EMERGENCY EQUIPMENT .1218. DOCUMENTATION & TECH PUBLICATIONS .1319. MAINTENANCE TRACKING PROGRAM .1320. NEW AIRCRAFT LIMITED WARRANTY.1321. CREW TRAINING AGREEMENT.151BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION
INTRODUCTION1. GENERAL DESCRIPTIONThis document is published for the purpose ofgeneral information for the evaluation of the design,performance and equipment of the Beechcraft BonanzaG36 aircraft. Should more detailed data be required, itcan be obtained by contacting:The Bonanza G36 is a single engine aircraft utilizingan all metal airframe. The aircraft has provisions forup to six occupants and their baggage. The aircraft iscertified for single pilot operation.Beechcraft CorporationP.O Box 85Wichita, Kansas 67201-0085Attention: Contracts Administration, Dept. 191Telephone: 316.676.7111Fax: 316.676.1910This document describes only the Bonanza G36aircraft, serial numbers E-4063 thru E-4080, itspowerplant and standard equipment. Also included arethe warranties applicable to the Bonanza G36 aircraft,Continental Motors engine, Garmin Avionics, Hartzellpropeller as well as the Bonanza G36 crew trainingagreement. In the event of any discrepancy betweenthis document and the Aircraft Purchase Agreementto which it may be appended, terms specified in theAircraft Purchase Agreement shall govern.Engine and Avionics warranties are subject to changeat the discretion of the manufacturer. BeechcraftCorporation does not warrant engines or avionics.Should the engine or avionics warranty reflected in thisdocument not be the current warranty provided by themanufacturer, Beechcraft Corporation disclaims anyliability to Buyer for any such error.The term “Aircraft” as used in this document and inthe Aircraft Purchase Agreement into which it maybe incorporated by reference shall unless otherwisedesignated include the entire Bonanza G36 aircraft andall of its parts, components and related publications,including manuals, as more fully described in thisSpecification and Description.The Bonanza G36 is powered by a Continental MotorsIO-550-B engine with a Hartzell constant-speed threebladed propeller mounted on the nose of the aircraft.The Bonanza G36 is certified in accordance with CARPart 3 Utility Category.DimensionsOverall Height .8 ft 7 in. (2.62 m)Overall Length .27 ft 6 in. (8.38 m)WingSpan (overall) .33 ft 6 in. (10.21 m)Area . 181 sq. ft (16.81sq. m)Sweep (at 25% chord) . 0.0 degDihedral . 6.0 degHorizontal TailSpan (overall) .12 ft 2 in. (3.71 m)Dihedral . 0.0 degCabinLength (including cockpit) .12 ft 7 in. (3.84 m)Height (max) .4 ft 2 in. (1.27 m)Width (max) .3 ft 6 in. (1.07 m)Entry DoorsFwd Cabin Door. 37 in. wide x 36 in. high. (0.94 m. wide x 0.91 m. high)Aft Utility Door. 45 in. wide x 35 in. high. (1.14 m. wide x 0.89 m. high)Throughout this document, Beechcraft Corporationreserves the right to revise the ‘Specification andDescription’ whenever occasioned by productimprovements, government regulations or other goodcause as long as such revisions do not result in asignificant reduction in performance standards.Copyright 2015 Beechcraft Corporation.All rights reserved.2
2. GENERAL ARRANGEMENT3BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION
3. DESIGN WEIGHTS AND CAPACITIESMaximum Ramp Weight . 3,663 lb (1,665 kg)Maximum Take-off Weight . 3,650 lb (1,659 kg)Maximum Landing Weight . 3,650 lb (1,659 kg)Basic Empty Weight * . 2,630 lb (1,193 kg)Fuel Capacity (Useable ) . 444 lb (202 kg)(@ 6.0 lb per U.S gallon)Limit SpeedsNever Exceed VNE. 205 KIAS (380 km/hr)Max Structural Cruising VNO. 165 KIAS (306 km/hr)Maneuvering VA . 141 KIAS (261 km/hr)Flap Extension SpeedsVFE (Approach) . 154 KIAS (285 km/hr)VFE (Full Down) . 124 KIAS (230 km/hr)* Estimated Basic Operating Weight includes standardinterior, prop de-ice, air conditioning, avionics,unusable fuel and oil.Landing Gear Operating and Extension Speeds4. PERFORMANCEForward Limit to 3,100 lb (1,409 kg) . 74 inForward Limit to 3,650 lb (1,659 kg) . 81 inAft Limit (at all weights) . 87.7 inAll performance data is based on a standard aircraft andInternational Standard Atmospheric (ISA) conditions.Take-off and landing lengths are based on level, hardsurface, dry runways with zero wind.Range (-3%) .910 nm (1,685 km)(1 pilot 2 passengers, VFR. Range allows for taxi,take-off, climb, cruise, descent and VFR fuel reserveof 45 minutes at Max. Range Power)Stall Speed (Flaps Down) . 58 kt (107 km/hr) IAS(at 3,650 lb/1,659 kg)Service Ceiling.18,500 ft (5,639 m)Take-off Field Length .1,913 ft (583 m)(Sea Level, ISA, 3,650 lb. / 1,659 kg.)Landing Distance .950 ft (290 m)(Sea Level, ISA, 3,650 lb. / 1,659 kg.)High Speed Cruise Speed (-3%) .176 kt (326 km/hr)(ISA, 6,000 ft (1,829 m) altitude, Max. Cruise Power25 In. Hg (or full throttle) @ 2,500 rpm)5. STRUCTURAL DESIGN CRITERIAThe Bonanza G36 wing and fuselage are of conventionalsemi-monocoque construction. It has fully cantileveredwings and empennage. Most of the structures arefabricated of high strength aluminum alloy. Steel andother materials are used as needed. The robustnessof the design philosophy has been validated overthousands of hours operation of airplanes in the fleet.Continuing structural integrity is ensured through aninspection program and appropriate maintenanceaction. The aircraft structure is divided into three majorcomponents, the fuselage, wing and empennage.VLO/VLE (retraction/extension). 154 KIAS (285 km/hr)CG Range6. FUSELAGEThe fuselage is fabricated of high strength aluminumalloy, with appropriate use of steel and other materials.The aircraft structure uses traditional methods ofaircraft design and validated through full scale fatiguetesting with no published life limits.The fuselage is shaped to provide optimized cabin roomand passenger comfort. A maximum internal cabin widthof 3 ft 6 in. (1.07 m) and maximum cabin height of 4 ft2 in. (1.27 m) is provided.CabinThe cockpit seating area, passenger seating areaand rear baggage area comprise the cabin portion ofthe fuselage. The pilot’s entry door is located on theforward right side of the fuselage while the passengersenter the cabin through the aft utility door on the rightrear side of the fuselage.The standard seating configuration consists of clubseating in the cabin, with the 3rd and 4th seats facingaft and the 5th and 6th seats facing forward.Utility DoorsThe utility doors, located on the aft right side of thecabin, provide for loading and unloading of passengersand baggage. The aft door must be closed first. Theforward door cannot be closed until the latch of the aftdoor is latched and flush with the edge of the door.After the forward door is closed it can be latched fromthe outside by rotating a half-moon shaped handle tothe closed position. A conventional handle of the insideof this door provides for opening or closing from theinside.4
Baggage CompartmentThe baggage compartment is accessible throughthe utility doors on the right side of the fuselage. Thebaggage area extends aft of the rear seats.Tail SectionThe tail section contains the emergency locatortransmitter.Windshield and Cabin WindowsThe windshield and cabin windows are Plexiglas. Thewindshield is a one-piece wrap-around style. Fourside windows are located in each side of the fuselage.The pilot’s side window incorporates a spring-latchedweather window. The forward square passengerwindows may be opened for ground ventilation andemergency egress.7. WINGThe wing is of semi-monocoque constructionincorporating dual spar structures from wing tip to wingtip. The front and rear spars are similar in constructionconsisting of upper and lower cap extrusions, stiffenersand webs. The inboard section of each spar consistsof a combination of channel fittings, assembled back toback, made from 7075 aluminum plate and forging forthe front and rear spar fittings. The wings are attachedto the wing center section at these fittings using eightbolts. Flaps and ailerons are installed on the wing.The flaps are hinged to the trailing edges of the wing.The flaps consist of a single spar, ribs, side plates andskins.The wing flaps are operated using an electric flapmotor. The flap system is operated by a flap controllever located on the co-pilots sub-panel. The flapcontrol lever has three positions: Up (0 ), Approach(12 ) and Down (30 ).A ‘two-in-one’ Position/Anti-collision light is located ineach wingtip.8. EMPENNAGEThe empennage consists of a vertical stabilizer anda fixed incidence horizontal stabilizer. Elevators areattached to the trailing edge of the horizontal stabilizerand are operated through a cable/pulley assemblyconnected to the control column. The rudder isattached to the trailing edge of the vertical stabilizer.A rudder trim tab is attached to the lower trailing edgeof the rudder.A red flashing beacon is located on top of the verticalstabilizer.59. LANDING GEARThe Bonanza G36 is equipped with retractable tricyclelanding gear. The main landing gear uses conventionalair over oil struts and retracts inwards into the wing. Thenose gear uses a conventional air over oil shock strutand retracts aft into the nose section. The landing gearis electrically controlled and actuated and is enclosedby mechanically actuated doors.The landing gear position and warning system providesvisual and aural indications of landing gear position.Three green indicator lights are located adjacent to thelanding gear control handle.Alternate landing gear extension is accomplished bya manual system that requires the landing gear to bewound down using a crank handle behind the frontseats.Nosewheel SteeringNosewheel steering is mechanically actuated by therudder pedals to provide directional control on theground. The minimum wing tip turning radius, usingpartial braking action is 27 feet 6 inches.BrakesThe airplane is equipped with hydraulically operatedbrake assemblies, one at each main gear wheel. Thebrakes are applied by toe pressure on the pilot’s orco-pilot’s rudder pedals. The parking brake T-handlecontrol is located on the lower left sub-panel.10. POWERPLANTThe Bonanza G36 is powered by one Continental MotorsCorporation model IO-550-B, normally aspirated,fuel-injected, direct drive, air-cooled, horizontallyopposed, 6-cylinder, 550-cubic-inch displacement, 300horsepower engine.Engine starts may be made using the aircraft batteryor external power.Throttle, Propeller and Mixture ControlsThe control levers are grouped along the upperportion of the pedestal. Pushing forward on a controllever increases its appropriate function, pulling backdecreases it. The knobs on the levers are shaped tostandard FAA configuration so they can be identifiedby touch. The controls are centrally located for ease ofoperation from either the pilot’s or copilot’s seat.Cowl FlapsThe cowl flaps are controlled by a manual control leverlocated on the center console. The cowl flap is closedwhen the lever is in the up position and open when thelever is down.BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION
11. PROPELLERElectrical SystemThe Bonanza G36 is equipped with a Hartzell constantspeed, variable pitch propeller, with three aluminumalloy blades.The airplane electrical system is a 28-vdc (nominal)system with the negative lead of each power sourcegrounded to the main airplane structure. DC electricalpower is provided by the following sources.Propeller RPM is controlled by a governor whichregulates hydraulic oil pressure to the hub. A controllever on the center pedestal allows the pilot to selectthe governor’s RPM range.If engine oil pressure is lost, the propeller will go tothe full high RPM position. This is because propellerlow RPM is obtained by governor-boosted engineoil pressure working against the centrifugal twistingmoment of the blades.12. SYSTEMSFlight ControlsDual flight controls are provided. The control wheelsare interconnected and provide aileron and elevatorcontrol. The primary control system is of conventionaldesign and is manually operated through control cables,push-pull rods and mechanical linkages providing pitch,roll and yaw. Pitch attitude of the aircraft is controlled bythe elevators. Roll is controlled through the ailerons.The secondary control system provides manual andelectric trim for the pitch system and roll trim from themanually operated roll trim surfaces.Flaps are attached to the rear spar and hinged to allowdownward movement. The wing flaps are electricallyactuated. The flap system is controlled by a flap controllever located on the center pedestal.Fuel SystemThe Bonanza G36 features a conventional, capacityfuel system requiring minimum management.The engine is designed to operate on aviation gasolinegrade 100LL (blue) or grade 100 (green). However, theuse of grade 100LL is preferred.The fuel capacity consists of two 40-gallon cells (37gallons usable.) A visual measuring tab is attached toeach filler neck of each individual cell.The fuel system is drained at 3 locations: one undereach wing just outboard of the fuselage, and a systemlow spot drain in the bottom of the fuel selector valve.These fuel drains are snap-type valves which areactuated by pushing up and twisting on the valve andthen releasing when the desired amount of fuel hasbeen drained.Battery 1 is a 10 amp-hour, 24 volt, lead acid batterylocated on the right forward side of the firewall. Battery2 is a 3.5 amp-hour, 24 volt. Sealed lead acid batterylocated on the cabin side of the firewall.Alternator 1 is a 100-amp, 28.5 volt, gear-drivenalternator located in from of the right forward cylinder.The alternator will deliver 100 amps at 2300 RPM andabove. It is capable of supplying power to the entireelectrical system. Alternator 2 is a 20-amp, 28.5 volt,gear driven alternator located at the rear of the engine.The alternator is capable of supplying power only toBus 2.Standby Power for the Standby Attitude Indicator – asealed lead acid battery is attached to the back of theStandby Attitude Indicator. If power is lost to Bus 1, (orto Left Circuit Breaker Panel 1B powered by Bus 1) thisbattery will power the standby attitude indicator for aminimum of one hour if the battery is fully charged.The electrical system is protected by current limiters,circuit breakers and circuit breaker type switches.All exterior lights are Light Emitting Diode (LED) type.External Power ReceptacleThe external power receptacle is located on the rightside of the engine cowling, connecting a 28-vdcexternal power unit to the airplane.Cabin EnvironmentThe environmental system consists of air conditioning,heating and ventilation systems, and their associatedcontrols.Air Conditioning and HeatingCabin temperature control is provided by a fullyautomatic climate control system. Conditioned air issupplied by a vapor cycle air conditioning system whichutilizes an engine-driven compressor, in conjunctionwith condenser and evaporator units installed insidethe tail cone. It is approved for operation in all phasesof flight, including takeoff. Both cabin cooling andheating are controlled by a fully-automatic ElectronicControl Unit.6
A single Transponder A single Magnetometer A Flight Director/Autopilot System that is integral tothe GIA and the autopilot servo units.Garmin Synthetic VisionThe control unit has “set and forget” functionality, allowingthe operator to select the desired cabin temperature,which will be automatically maintained. The systemautomatically switches between conditioned or heatedair as necessary to maintain the selected temperature.Conditioned air is distributed to aft cabin passengersthrough the overhead PSU panel, while cockpitoccupants receive air via enlarged overhead vents formaximum cooling. Heated air is distributed by firewalland aft spar cover vents. Aft cabin passengers havetheir own heat setting available to them on the ceilingconsole. The new control is a rocker switch with anLED indicator of heat position. This is accessible tothe aft cabin passengers as well as being within reachof the pilot, just behind the ceiling speaker.The Garmin Synthetic Vision (SV) system blends information about the aircraft’s position with topographicdatabases to create and display 3D images which aredisplayed on the PFD. Land, water and sky are differentiated with shading and textures that are similarto the topographical colors found on the multi-functiondisplay (MFD) moving map. SV works to alert pilotsof potential ground hazards by displaying terrain andobstacles which pose a threat to the aircraft with appropriate TAWS alert coloring.Features of the Synthetic Vision system include: Obstacles: Enlarges obstacle(s) as aircraftapproaches; TAWS based colors are used when therequired obstacle clearance is not met or in the caseof potential obstacle impact. Traffic: TCAS traffic symbology represented in 3Dthat changes size relative to range. Flight Path Marker: Displays projected path of theaircraft. Zero Pitch Line: Distinguishes aircraft’s altitude inrelation to nearby terrain.13. FLIGHT COMPARTMENT AND AVIONICS Gridlines: Drawn on the terrain surface.The Bonanza G36 is certified for single pilot operation. Runways: Runway designations and thresholds aresuperimposed on terrain data.The Garmin G1000 Integrated Avionics System is a fullyintegrated flight, engine, communication, navigation,autopilot an surveillance instrumentation system. Thesystem consists of a Primary Flight Display (PFD),Multi-Function Display (MFD) and Audio Panel (GMA)that make up the instrument panel. Line ReplacableUnits (LRUs) that are included in the above displaysand controls the following: A single Air Data Computer (ADC) A single Attitude and Heading Reference System(AHRS) A single Engine/Airframe Processing Unit (GEA) Two Integrated Avionics Units (GIA)7 Airport Signs: Depicts identifier of nearby airportsPrimary Flight Display System (PFD) Garmin Display Unit (GDU 1040)The Primary Flight Display (PFD) is a 10.4 inch LiquidCrystal Display (LCD). It displays airspeed, attitude,altitude, and heading information in a traditionalformat. A vertical speed display is located to the rightof the altitude display. A crew alerting window andannunciation window are available for display. Slipinformation is shown as a trapezoid under the bankpointer. Rate of turn information is shown on the scaleabove the compass rode. Full scale deflection is equalto a standard rate turn.BONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION
Bonanza G36 Main Instrument Panel12345678131211101. Primary Flight Display (PFD)8. Standby Altimeter2. Master Audio Panel9. Storage Compartment3. Standby Compass10. Circuit Breaker Panel4. Multi-Function Display (MFD)11. Flap Position Indicators5. Standby Airspeed Indicator12. Landing Gear Position Indicators6. Standby Attitude Indicator13. Pilot Sub-panel97. ELT switch8
The PFD incorporates controls for communications,navigation, altimeter control and Flight Managementfunctions. Trend vectors are shown on the airspeed andaltimeter displays as a magenta line which predicts theairspeed or altitude 6 seconds in the future assumingthe current rate of change in maintained. The turn rateindicator also functions as a trend indicator on thecompass scale.Air Data Computer (ADC) Garmin Air Data Computer (GDC 74A)Multi-Function Display System (MFD)Magnetometer (GMU) Garmin Magnetometer Unit (GMU 44) Garmin Display Unit (GDU 1045)The Multi-Function Display (MFD) is a 10.4 inch LiquidCrystal Display (LCD). It displays engine data, maps,terrain, traffic and topography displays, and flightplanning and progress information. It also controls anddisplays weather data link information, lightning strikeinformation and audio entertainment features. Thedisplay unit is identical to the PFD and contains thesame controls plus the addition of autopilot controls.Discrete engine sensor information is processed bythe Garmin Engine/Airframe (GEA) sub-system. Whenan engine sensor indicates a value outside the normaloperating range, the legend on the MFD will turn yellowfor the caution range and red for the warning range.Master Audio Panel (GMA) Garmin Master Audio Panel (GMA 1347)The audio panel provides pilot and copilot microphoneselection of communication radios and audio selectionfor all communication and navigation receiver radios.The audio panel has volume controls for both pilot andcopilot. There are controls for speaker on/off selectionand interphone mode selection. If power is lost to theaudio panel, the pilot’s headset and microphone areconnected directly to COMM 1. An internal clearancerecorder can play back the last 2½ minutes of receivedCOMM audio. A marker beacon receiver is alsocontained within the audio panel with visual informationprovided on the PFD.The Air Data Computer is connected to the pitot andstatic air system and an Outside Air Temperature(OAT) probe which is located on the bottom of the leftwing. The ADC provides OAT, airspeed, altitude andvertical speed for pilot displays and Flight ManagementSystem (FMS) functions.The Magnetometer senses the earth’s magneticfield and provides this information to the AHRS forprocessing to determine the airplane’s magneticheading. The GMU 44 is located in the left wingtip areaand is powered by the AHRS.Attitude and Heading Reference System (AHRS) Garmin Attitude and Heading Reference System(GRS 77)The Attitude and Heading Reference System providespitch, roll, heading and angular rate information forpilot display and for FMS calculations.Engine/Airframe Interface Unit (GEA) Garmin Engine/Airframe Interface Unit (GEA 71)The Engine/Airframe Interface Unit provides input andoutput for engine and airframe sensors and systems.The GEA has inputs for the following signals: Manifold Absolute Pressure (MAP) Engine RPM Fuel Flow Six Cylinder Head temperature (CHT) probes Six Exhaust Gas Temperature (EGT) probes Oil Temperature Oil Pressure Alternator 1 LoadIntegrated Avionics Units (GIA) Alternator 2 Load Garmin Integrated Avionics Unit (GIA 63/63W) Bus 1 VoltageTwo Integrated Avionics Units are installed. BothGIAs provide interfaces to all Line Replaceable Units(LRUs) in the G1000 system. Each GIA contains aVHF COMM, VHF NAV, glideslope and WAAS enabledGPS functions including LPV/LNAV/VNAV. GIA 1provides autopilot mode control and servo controland monitoring. GIA 2 provides servo control andmonitoring. Bus 2 Voltage9 Fuel Quantity Left Tank Fuel Quantity Right Tank Starter Engaged Utility Door Switch Air Conditioning Condenser positionBONANZA G36 (E-4063 THRU E-4080) / BEECHCRAFT CORPORATION
This information is used to display Engine and Systeminformation on the left side of the MFD and alerts inthe annunciation window of the PFD. A discrete outputfrom the GEA is used to control the bus tie relay thatconnects electrical Bus 1 to Bus 2.Engine Indicating SystemEngine information is available in a vertical arrangementalong the left side of the MFD. In reversionary mode,this information will also be generated along the leftside of the PFD.Engine DisplayThe engine display page is the default display andshows left and right manifold pressure, engine RPMwith prop-sync, fuel flow, cylinder head temperature,oil temperature, oil pressure, alternator load, fuel tankquantity.The left and right manifold pressure is the absolutepressure in the engines manifold and is calibratedin inches of mercury. A circular scale with a pointerprovides overall manifold indication with numeric valuejust below. A manifold pressure sensor located on eachinduction manifold is wired to the left and right GEAunits for display information. By observing the manifoldpressure and adjusting the propeller and throttle controls,the power output of the engine can be adjusted.The left and right circular scale with a pointer providesoverall engine speed in revolutions per minute (RPM),with numerical value just below. A transducer attachedto the engine sends electronic signals to the left andright GEA units for display information.Fuel flow is indicated on a linear scale with a numericreadout in gallons per hour above and to the scale leftand right. A turbine rotor installed in the fuel line rotatesin proportion to the fuel flow.Alerting SystemThe G1000 provides an Annunciation window andan Alerts window on the PFD to inform the pilots ofWarning Alerts, Caution Alerts, Advisory Alerts andMessages that may occur during the operation of theairplane. Both windows are also available on the MFDto provide the same notifications when the MFD isoperating in reversionary mode.When an alertsimultaneously.occurs,threethingshappeni). The ALERTS softkey will assume a new label andcolor depending on the level of the alert. The softkeylabel will change to a red WARNING label for warningalerts, a yellow CAUTION label for caution alerts anda white ADVISORY label for advisory alerts. The labelwill also assume a flashing mode.ii). An aural tone will be provided for Warning Alertsand Caution Alerts.iii). An annunciation with the same color as the alertslabel is displayed in the Annunciation Window.Autopilot Garmin Automatic Flight Control System (AFCS)(GFC 700)The GFC 700 AFCS consists of the followingcomponents:i). The following mode control keys on the MFD: AP (Autopilot engage/disengage) YD (Yaw Damp engage/disengage)Cylinder head temperature is indicated on a linearscale with a left and right indicator. The hottest of the sixcylinders for each engine is displayed and is identifiedby the numeric value inside the pointer. All six cylinderheads for each engine have temperature probes thatare wired to the left and right GEA units. These can bedisplayed by accessing the LEAN engine page. FD (Flight Director On/Off)Oil temperature is indicated on a linear scale and issensed as it enters each engine from the oil cooler.The sensors are wired to the left and right GEA fordisplay. Numeric temperature value is displayed on theSYSTEM engine page. VNV (Vertical nav mode Selects/Deselects (ifinstalled)Oil pressure is sensed at the back of each engine off aport below the oil coolers and wired to the left and rightGEA for display. The display is linear, with a numericpressure value available on the SYSTEM engine page. HDG (Heading Mode On/Off) NAV (Nav Mode On/Off) APR (Approach Mode On/Off) ALT (Altitude Mode On/OFF) FLC (Flight Level Change Mode On/Off) NOSE UP and NOSE DN (vertical mode referencechange)ii). A two-segment pitch trim, switch located on the leftside of the pilots control wheel.10
iii). A red autopilot-disconnect and pitch-trim-interruptswitch (AP DISC/TRIM INTER) located on the leftside of the pilot’s control wheel. Pressing this switchalso acknowledges a manual or automatic autopilotdisconnect by cancelling the tone and flashing APannunciator.Terrain Awareness and Warning System (TAWS)iv). A Control Wheel Steering Switch (CWS) located onthe left side of the pilot’s control wheel. Reduced Required Terrain (RTC) and Obstacle(ROC) clearance cautions and warnings.v). A Go-Around switch located on the left side of thethrottle. Imminent Terrain (ITI) and Obstacle (IOI) Impactcautions and warnings.vi). Servos with autopilot processing logic in thepitch, pitch trim and roll control systems. A servowith independent processing logic for the Yaw Dampfunction.The Garmin TAWS is a Class B system as defined byTSO-C151b and provides the following functions.i) Forward Looking Terrain Avoidance (FLTA) alertswhich include:ii). Premature Descent Alerts (PDA)iii). The following basic Ground Proximity WarningSystem (GPWS) functions:vii). Servo mounts and brackets. Excessive Descent Rate (EDR) Alertviii). Flight Director processing logic is contained in thetwo inte
1 bonanza g36 (e-4063 thru e-4080) / beechcraft corporation this document is published for the purpose of providing general information for the evaluation of the design, performance and equipment of the bonanza g36.
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