Beechcraft Baron G58 Pilot Operating Handbook Download | Manualshive

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Limitations

Section 2

Model G58

2-13

PROPELLER DEICE AMMETER

Normal Operating Range (Green Arc) . . . . . . . . 14 to 18 amps

WEIGHT LIMITS

Maximum Take-off . . . . . . . . . . . . . . . . . . . . . . . . . . .  5500 lbs
Maximum Landing  . . . . . . . . . . . . . . . . . . . . . . . . . . .  5400 lbs
Maximum Ramp   . . . . . . . . . . . . . . . . . . . . . . . . . . . .  5524 lbs

Maximum Baggage Compartment Weights:
Main Cabin Compartment
(less occupants and equipment). . . . . . . . . . . . . . . . . .  400 lbs
Extended Aft Compartment  . . . . . . . . . . . . . . . . . . . . .  120 lbs
Nose Compartment
(baggage and equipment combined) . . . . . . . . . . . . . .  300 lbs

Refer to Section 6, WEIGHT AND BALANCE/EQUIPMENT
LIST for additional information.

CENTER OF GRAVITY
(LANDING GEAR EXTENDED)

Forward Limits: 74.0 inches aft of datum at 4200 lbs and
under, then straight line variation to 78.0 inches aft of datum at
gross weight of 5400 lbs (maximum landing weight) and 78.3
inches aft of datum at gross weight of 5500 lbs.
Aft Limit: 86 inches aft of datum at all weights.

REFERENCE DATUM

Datum is 83.1 inches forward of center line through forward
jack points.

MEAN AERODYNAMIC CHORD

MAC leading edge is 67.2 inches aft of datum.
MAC length is 63.1 inches.

May, 2015

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Summary of Contents for Baron G58

Page 1: ......

Page 2: ...epartment s Bureau of Export Administration at 202 482 4811 or visit the US Department of Commerce website Any Raytheon marks contained in this document are owned by Raytheon Company and are employed pursuant to a limited license granted by Raytheon Company Prior to March 26 2007 Beechcraft Corporation was owned by Raytheon Company but is no longer affiliated wtih Raytheon Company Beechcraft Corpo...

Page 3: ...ved Airplane Flight Manual P N 58 590000 67 Revision A12 May 2015 Title Page May 2015 Logo Page Undated List Of Effective Pages May 2015 Log Of Revisions Revision A12 May 2015 Revision A11 July 2014 Revision A10 August 2013 Revision A9 April 2012 Revision A8 June 2011 Revision A7 December 2009 Revision A6 February 2009 Revision A5 December 2008 Revision A4 April 2008 Revision A3 March 2007 Revisio...

Page 4: ...0 thru 3A 26 April 2008 4 1 thru 4 4 June 2011 4 5 thru 4 9 April 2008 4 10 and 4 11 December 2008 4 12 thru 4 21 April 2008 4 22 August 2013 4 23 thru 4 27 April 2008 4 28 thru 4 29 June 2011 4 30 April 2012 4 31 thru 4 56 June 2011 5 1 thru 5 54 July 2014 6 1 thru 6 22 December 2009 7 1 thru 7 98 May 2015 8 1 thru 8 34 April 2008 9 1 and 9 2 November 2005 Supplements See Log of Supplements 10 1 ...

Page 5: ... use of the PIT mode affects ABNORMAL and NOR MAL PROCEDURES sections Rescinded when Service Bulle tin 22 3795 has been complied with Temporary Change not applicable to TH 2159 and after June 2006 58 590000 67TC2 Adds TAWS limitations regarding flight over large bodies of sea level water May 2008 58 590000 67TC3 Incorporated into the 58 590000 67A7 revision Please discard all 58 590000 67TC3 pages...

Page 6: ...t of the manual immediately in front of the Log Of Revisions page s This page replaces any Log Of Temporary Changes page dated prior to the date of this Log 58 590000 67TC5 Incorporated into the 58 590000 67A8 revision Please discard all 58 590000 67TC5 pages 1 of 4 thru 4 of 4 Incorpo rated PART NUMBER SUBJECT DATE ...

Page 7: ...TH 2158 not in compliance with S B 22 3795 Description of Change Uncommanded pulsing of the control column during overly aggressive autopilot captures and during use of the PIT mode affects and ABNORMAL and NORMAL PROCEDURES Sections Filing Instructions Insert the following pages of this temporary change into the Model G58 Pilot s Operating Handbook and FAA Approved Airplane Flight Manual and reta...

Page 8: ...vice Bulletin 34 3774 without terrain database 08T2 or later database installed Description of Change Adds limitation regarding flight over large bodies of sea level water Filing Instructions Insert pages 1 of 4 and 2 of 4 of this temporary change into the Model G58 Pilot s Operating Handbook and FAA Approved Airplane Flight Manual following the Log of Temporary Changes Insert pages 3 of 4 and 4 o...

Page 9: ......

Page 10: ...w Section 1 All Reformatted to change Hawker Beechcraft Corporation to Beechcraft Corporation 1 1 and 1 2 Revised Table of Contents 1 10 Revised AIRPLANE THREE VIEW 1 12 and 1 13 Revised PROPELLER MANUFACTURER and PROPELLER TYPE Added PITCH SETTINGS and PROPELLER DIAMETER Shifted data Section 2 All Reformatted to change Hawker Beechcraft Cor poration to Beechcraft Corporation 2 1 thru 2 4 Revised ...

Page 11: ...LLER MANUFACTURER PRO PELLER TYPE and PROPELLER DIAMETER Shifted data 2 18 Revised website reference Section 7 All Reformatted to change Hawker Beechcraft Corporation to Beechcraft Corporation 7 1 thru 7 6 Revised Table of Contents 7 31 Revised PROPELLERS Shifted data PAGE DESCRIPTION A12 ...

Page 12: ...ved Airplane Flight Manual P N 58 590000 67 Revision A11 July 2014 PAGE DESCRIPTION Title Page New LOEP New LOR New Section 5 All Reformatted to change Hawker Beechcraft Cor poration to Beechcraft Corporation 5 24 Added note to Manifold Pressure vs RPM graph CONTINUOUS OPERATION AT PEAK EGT IS PERMITTED A11 ...

Page 13: ... Operating Handbook and FAA Approved Airplane Flight Manual P N 58 590000 67 Revision A10 August 2013 PAGE DESCRIPTION Title Page New LOEP New LOR New Section 4 4 22 Revised Step 4 of CRUISE procedure to refer ence Leaning Using EGT Indication in Other Nor mal Procedures A10 ...

Page 14: ...New Section 1 1 18 Revised definition of OAT Section 4 4 30 Revised Step 3 of the LEANING USING THE EXHAUST GAS TEMPERATURE EGT INDICATION procedure Section 5 5 1 thru 5 4 Corrected Table of Contents 5 12 Replaced references to IOAT with references to OAT 5 24 MANIFOLD PRESSURE vs RPM graph removed NOTE and revised Not Recom mended for Cruise Power Settings area of graph to include all engine spee...

Page 15: ...and 5 43 Removed 2100 rpm data from Range Profile 166 Gallons graphs Shifted data 5 44 and 5 45 Removed 2100 rpm data from Endurance Profile 166 Gallons graphs Shifted data 5 46 and 5 47 Removed 2100 rpm data from Range Profile 194 Gallons graphs Shifted data 5 48 and 5 49 Removed 2100 rpm data from Endurance Profile 194 Gallons graphs Shifted data 5 50 thru 5 54 Shifted data Section 7 7 1 thru 7 ...

Page 16: ...C New LOR New Section 1 1 13 Incorporated 58 590000 67TC4 Chinese Avia tion Gasoline 1 23 Changed Generic to Generic Added LNAV LPV RNAV and SBAS to Acronyms Shifted data 1 24 Changed Garmin to Garmin Shifted data Section 2 2 8 Incorporated 58 590000 67TC4 Chinese Avia tion Gasoline 2 17 Revised the Approved Airframe System Software Versions for the Garmin G1000 Integrated Sys tem Shifted data 2 1...

Page 17: ...ORING RAIM Section 4 4 1 thru 4 4 Revised Table of Contents 4 28 Added a colon Shifted data 4 29 and 4 30 Incorporated 58 590000 67TC5 Leaning using EGT Shifted data 4 31 thru 4 34 Shifted data 4 35 Changed back ground to background Shifted data 4 36 thru 4 41 Shifted data 4 42 Changed Versions to Version Changed and to or 2 places Shifted data 4 43 Changed and to or Shifted data 4 44 Changed Vers...

Page 18: ...ision A8 June 2011 7 50 thru 7 53 Shifted data 7 69 Changed Versions to Version Changed and to or 7 74 Changed and to or 7 80 Changed and to or Removed precision Added approach with 7 83 Changed Versions to Version Changed and to or PAGE DESCRIPTION A8 ...

Page 19: ...ntents 1 12 Added supplement AFMS 20002 1 1 13 Removed Pitch Settings and Propeller Diameter 1 15 Incorporated 58 590000 67TC3 Added Two Engines 2 1 thru 2 4 Revised Table of Contents 2 9 Revised Propeller Manufacturer Added supple ment AFMS 20002 1 Removed Pitch Settings and Propeller Diameter 2 22 Changed FM to FPM and 45 30 30 to 45 30 30 Section 5 ALL Changed Raytheon Aircraft Company to Hawke...

Page 20: ... Beechcraft Corporation 6 1 Corrected Table of Contents 7 31 Revised Propellers Added supplement AFMS 20002 1 7 49 Changed V to VDC 2 places 7 68 Changed Temperatures to Temperature 7 69 Added software versions 7 70 Changed are to is 7 74 Changed V to VDC 2 places 7 83 Added software versions and a comma 7 84 Changed Standby to standby and removed a period Added comma PAGE DESCRIPTION A7 ...

Page 21: ...RIPTION Title Page New LOEP New LOR New 2 3 Revised Table of Contents 2 16 Added Software Version 0857 06 2 17 Added Software Version 0857 06 2 20 Shifted data 2 21 Added Airframe System Software Ver sion 0857 06 Table and shifted data 2 22 Shifted data 2 23 Changed Limit to limit and shifted data 2 24 Shifted data 2 25 Changed equiped to equipped and shifted data 2 26 Shifted data A6 ...

Page 22: ...quipment List and shifted data 2 43 Shifted data 2 44 Revised Shoulder Harness crew compart ment entry in the Kinds of Operations Equip ment List and shifted data 4 41 thru 4 43 Added Software Version 0857 06 4 44 Changed airplane to aircraft 7 49 Added Software Version 0857 06 7 67 Changed earth s to Earth s 7 69 Added Software Version 0857 06 7 74 Added Software Version 0857 06 7 80 Added Softwa...

Page 23: ...ifold pressure 3A 13 thru 3A 17 Inserted Cabin Heater and Wing Ice Light procedures Shifted data 4 3 and 4 4 Inserted Cabin Heater procedure and updated RAC to Hawker Beechcraft 4 10 Inserted Cabin Heater Over Tempera ture Switch Heater Exhaust Outlet Heater Fuel Drain Line Procedures 4 11 Shifted data 4 49 Inserted Cabin Heater Procedure 4 50 thru 4 53 Shifted data 4 55 Corrected flyover noise le...

Page 24: ...sion Service Supplements Engine Controls and Instrument Terminology and Reformatted 1 23 and 1 24 Revised Acronyms and Reformatted 2 1 thru 2 4 Revised Table of Contents and Reformatted 2 5 thru 2 15 Revised Engine Type Engine Operating Limita tions Oil Pressure Fuel Quantity and Refor matted 2 16 thru 2 27 Revised General Garmin G1000 Integrated Avionics System Reformatted and Shifted Data 2 28 t...

Page 25: ...ted 3A 4 thru 3A 5 Reformatted and Shifted Data 3A 6 Revised Starter Engage L START ENGD or R START ENDG Shifted Data and Reformatted 3A 7 thru 3A 17 Added Circuit Breaker Tripped Revised Engine and or Fuel Display Failure Shifted Data and Reformatted 3A 18 and 3A 19 Added Failed Heading During Ground Opera tions Failure of Cooling Fans PFD FAN FAIL MFD FAN FAIL or AVIONICS FAN Advisory Message Sh...

Page 26: ...hru 7 11 Revised Illustrations and Reformatted 7 12 thru 7 48 Revised Warning Horn and GEAR UP Annunci ation Propellers Propeller Sync Pointer Propeller Synchronizer Tables and Reformatted 7 49 thru 7 51 Revised Table and Reformatted 7 52 thru 7 64 Revised Cabin Heating Electrothermal Propel ler Deice General and Reformatted 7 65 thru 7 72 Revised Primary Flight Display PFD Multi functional Displa...

Page 27: ...cing Pub lications Airplane Inspection Periods Alterations or Repairs to the Airplane Fuel Cells and Reformatted 8 19 thru 8 34 Revised Batteries Tires Brakes Heating and Ventilating System Alternators Exterior Painted Surfaces Magnetos Consumable Materials Lamp Replacement Guide and Reformatted A4 PAGE DESCRIPTION ...

Page 28: ...Operating Handbook and FAA Approved Airplane Flight Manual P N 58 590000 67 Revision A3 March 2007 PAGE DESCRIPTION Title Page Revised for Company Name Change Logo Page Revised for Company Name Change LOEP Revised for Company Name Change LOR Revised for Company Name Change A3 ...

Page 29: ...ce 1 12 Revised Propeller Manufacturer 1 19 Revised Engine Controls and Instruments Termi nology 2 17 Revised Garmin G1000 Integrated Avionics Sys tem 2 21 Revised GPS Navigation 2 27 Added Placard 2 28 thru 2 33 Deleted Placards and Shifted Data 2 34 Added Placard and Shifted Data 2 35 thru 2 38 Revised Kinds of Operations Equipment List and Shifted Data 3 11 Revised Electrical Smoke or Fire 3 14...

Page 30: ...on 4 12 and 4 13 Revised Before Engine Starting 4 15 Revised Before Taxi 4 32 Revised Autopilot Flight Director Procedures 4 42 Revised Preflight Inspection 6 15 Revised Loading Computing Procedure 6 17 and 6 18 Revised Weight and Balance Loading Form 7 1 and 7 2 Reprinted 7 3 thru 7 6 Revised Table of Contents 7 7 Revised Seating Arrangements 7 8 thru 7 10 Reprinted 7 11 Revised Illustration 7 12...

Page 31: ...netometer GMU and Shifted Data 7 70 and 7 71 Revised Engine Display and Shifted Data 7 72 thru 7 74 Revised Alerting System and Shifted Data 7 75 thru 7 90 Revised Autopilot and Shifted Data 7 91 Revised PDA Premature Descent Alert TOO LOW TERRAIN and Shifted Data 7 92 and 7 93 Revised Excessive Descent Rate EDR Alert and Shifted Data 7 94 thru 7 96 Revised Stormscope if installed Emergency Locato...

Page 32: ...1 thru 2 4 Revised Table of Contents 2 12 Revised Weight Limit 2 24 thru 2 26 Added Garmin Terrain Awareness and Warning System TAWS and Shifted Data 2 27 thru 2 31 Added Placard Shifted Data 2 32 thru 2 40 Revised Illustration and Shifted Data 3 1 and 3 2 Revised Table of Contents 3 11 Revised Electrical Smoke or Fire 3 20 thru 3 26 Added Garmin Terrain Awareness and Warning System TAWS and Shift...

Page 33: ...ta 4 22 Revised Cruise and Shifted Data 4 23 Revised Descent and Shifted Data 4 24 thru 4 27 Revised Balk Landing Shutdown and Secur ing Other Normal Procedures and Shifted Data 4 28 thru 4 38 Revised Shutdown and Shifted Data 4 39 thru 4 41 Revised Autopilot Flight Director Procedures and Shifted Data 4 42 Revised Preflight Inspection and Shifted Data 4 43 and 4 44 Revised After Starting and Shif...

Page 34: ...ility Doors Removed and Shifted Data 7 26 Revised Openable Cabin Windows Deleted Emergency Exits and Shifted Data 7 27 and 7 28 Revised Control Locks and Shifted Data 7 29 Revised Engines and Throttles Propellers and Mixtures and Shifted Data 7 30 Revised Engine Ice Protection and Shifted Data 7 31 and 7 32 Revised Propellers Propeller Sync Pointer Fuel Cells and Shifted Data 7 33 Revised Fuel Qua...

Page 35: ...tarters External Power and Shifted Data 7 50 thru 7 55 Revised Interior Lighting and Shifted Data 7 56 and 7 57 Revised Normal Static Air System Emergency Static Air System and Shifted Data 7 58 thru 7 63 Revised Stall Warning and Shifted Data 7 64 thru 7 68 Revised Primary Flight Display PFD and Shifted Data 7 69 thru 7 85 Revised Engine Display and Shifted Data 7 86 thru 7 96 Added Garmin Terrai...

Page 36: ...d Airplane Flight Manual P N 58 590000 67 Original Issue November 2005 PAGE DESCRIPTION Title Page LOEP L OR 1 1 thru 1 24 2 1 thru 2 38 3 1 thru 3 24 3A 1 thru 3A 20 4 1 thru 4 52 5 1 thru 5 58 6 1 thru 6 22 7 1 thru 7 84 8 1 thru 8 34 9 1 and 9 2 Supplements See Log of Supplements 10 1 thru 10 64 May 1994 A ...

Page 37: ...ents 1 8 Airplane Flight Manual Supplements Revision Record 1 9 Airplane Three View 1 10 Ground Turning Clearance 1 11 Descriptive Data 1 12 Engines 1 12 Number of Engines 1 12 Engine Manufacturer 1 12 Engine Model Number 1 12 Engine Type 1 12 Horsepower Rating 1 12 Number of Propellers 1 12 Propeller Manufacturer 1 12 Number of Blades 1 12 Propeller Type 1 12 Pitch Settings 30 Inch Station 1 13 P...

Page 38: ...rtificated Weights 1 15 Cabin and Entry Dimensions 1 15 Cabin Baggage Volumes 1 16 Specific Loadings At Maximum Take off Weight 1 16 Service Ceiling 1 16 Symbols Abbreviations and Terminology 1 16 General Airspeed Terminology 1 16 Meteorological Terminology 1 19 Power Terminology 1 20 Engine Controls and Instruments Terminology 1 20 Airplane Performance and Flight Planning Terminology 1 21 Weight ...

Page 39: ...ilots The Safety Information should be read and studied Periodic review will serve as a reminder of good piloting tech niques Use only genuine Beechcraft Corporation or Beechcraft Corporation approved parts obtained from Beechcraft Corporation approved sources in connection with the maintenance and repair of Beech airplanes Genuine Beechcraft Corporation parts are produced and inspected under rigo...

Page 40: ...ms any responsibility for malfunctions failures damage or injury caused by use of non Beechcraft Corporation approved parts IMPORTANT NOTICE This handbook should be read carefully by the owner and the operator in order to become familiar with the operation of the airplane Suggestions and recommendations have been made within it to aid in obtaining maximum performance without sac rificing economy B...

Page 41: ...rmity with all airworthiness requirements established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory for continued airworthiness and to maintain the airplane in a condition equal to that of its original manufacture Beechcraft Corporation Authorized Outlets can provide recom mended modif...

Page 42: ...rovide as complete cover age as possible applicable to any configu ration of the airplane some optional equipment has been included in the scope of the handbook However due to the vari ety of airplane appointments and arrange ments available optional equipment described or depicted herein may not be designated as such in every case Immediately following the Title Page is a List of Effective Pages ...

Page 43: ... text or an illustration which has been revised by the addition of or a change in information is denoted by a solid revision bar located adjacent to the area of change and placed along the outside margin of the page REVISION SERVICE The following publications will be provided at no charge to the registered owner operator of this airplane 1 Reissues and revisions of the Pilot s Operating Hand book ...

Page 44: ...ion of the airplane with optional equipment installed It shall be the responsibility of the owner operator to ensure that the latest revisions of publications referenced in this handbook are utilized during operation servicing and maintenance of the airplane SUPPLEMENTS When a new airplane is delivered from the factory the hand book delivered with it contains either an STC Supplemental Type Certif...

Page 45: ...approvals plus the new approval The supplemental material will be added to the Section in accordance with the sequence speci fied on the Log page NOTE Upon receipt of a new or revised supple ment compare the existing Log of Supple ments in the handbook with the corresponding applicable Log page accom panying the new or revised supplement It may occur that the Log page already in the handbook is da...

Page 46: ... G58 Section 1 1 10 AIRPLANE THREE VIEW TH01C 054511AB AI WING AREA 199 2 SQ FT 15 FT 11 IN 37 FT 10 IN 29 FT 10 IN 8 FT 11 IN 10 4 IN 9 FT 7 IN 9 FT 9 IN McCauley 77 INCH DIAMETER Hartzell 75 INCH DIAMETER May 2015 ...

Page 47: ...OUTSIDE GEAR 17 FT 6 IN RADIUS FOR INSIDE GEAR 7 FT 11 IN RADIUS FOR NOSE WHEEL 15 FT 6 IN RADIUS FOR WING TIP 31 FT 6 IN GROUND TURNING CLEARANCE TH00C 020334AA AI TURNING RADII ARE PREDICATED ON THE USE OF PARTIAL BRAKING ACTION AND DIFFERENTIAL POWER May 2015 ...

Page 48: ... injected direct drive air cooled six cylinder horizontally opposed 550 cubic inch displacement HORSEPOWER RATING 300 H P NUMBER OF PROPELLERS Two PROPELLER MANUFACTURER McCauley Propeller Vandalia Ohio or Hartzell Propeller Inc Piqua Ohio NUMBER OF BLADES Three PROPELLER TYPE McCauley Propellers Standard Constant speed variable pitch three blade propeller using a 3AF32C512 X hub with X 82NEA 5 bl...

Page 49: ...tional Constant speed variable pitch three blade propeller using a PHC J3YF 2UF hub with FC7391D K blades PITCH SETTINGS 30 INCH STATION McCauley Propellers Standard Low 15 2 0 2 Feathered 82 5 0 5 Hartzell Propellers Optional Low 12 8 0 2 High 18 5 1 0 Feathered 80 0 0 5 PROPELLER DIAMETER McCauley Propellers Standard Max 77 inches Min 76 5 inches Hartzell Propellers Optional Max 75 inches Min 73...

Page 50: ...tion Gasoline Grade 100 green Aviation Gasoline Grade 115 145 purple Chinese Aviation Gasoline RH 95 130 Chinese Aviation Gasoline RH 100 130 FUEL CAPACITY STANDARD SYSTEM Total Capacity 200 Gallons Total Usable 194 Gallons OPTIONAL SYSTEM Total Capacity 172 Gallons Total Usable 166 Gallons May 2015 ...

Page 51: ... a list of approved oils When operating temperatures overlap indicated ranges use the lighter grade of oil MAXIMUM CERTIFICATED WEIGHTS Maximum Take off Weight 5500 lbs Maximum Landing Weight 5400 lbs Maximum Ramp Weight 5524 lbs CABIN AND ENTRY DIMENSIONS Cabin Length 12 ft 7 in Cabin Width max 3 ft 6 in Cabin Height max 4 ft 2 in Fwd Cabin Door 37 in wide x 36 in high Aft Utility Door 45 in wide...

Page 52: ...ble within this handbook GENERAL AIRSPEED TERMINOLOGY CAS Calibrated Airspeed is the indicated airspeed of an airplane corrected for position and instrument error Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level GS Ground Speed is the speed of an airplane relative to the ground IAS Indicated Airspeed is the speed of an airplane as shown on the airspeed indicator wh...

Page 53: ...ion and most rearward C G For some conditions of weight and altitude stall can be encountered at speeds above VMCA as established by the certification procedure described above in which event stall speed must be regarded as the limit of effective directional control VSSE Intentional One Engine Inoperative Speed is a speed above both VMCA and stall speed selected to provide a margin of lateral and ...

Page 54: ...t that may not be exceeded at any time VNO or VC Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution VS Stalling Speed or the minimum steady flight speed at which the airplane is controllable VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration VX Best Angle of...

Page 55: ...2 millibars 4 The temperature gradient from sea level to the altitude at which the temperature is 56 5 C 69 7 F is 0 00198 C 0 003566 F per foot and zero above that altitude OAT Outside Air Temperature is the free air static temperature obtained either from the temperature indicator IOAT adjusted for compressibility effects or from ground meteorological sources Pressure Altitude Altitude measured ...

Page 56: ...ttings recommended for cruise Recommended Cruise Intermediate power settings for which cruise power settings are presented Take off and Maximum Continuous Highest power rating not limited by time To be used only for conditions which warrant the use of this rating EGT The Exhaust Gas Temperature Display is used to identify the lean and best power fuel flow mixtures for various power settings during...

Page 57: ...e propeller in revolutions per minute RPM Throttle Control Used to control power by introducing fuel air mixture into the intake passages of an engine Settings are reflected by readings on the manifold pressure display Accelerate Stop Distance The distance required to accelerate an airplane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the ai...

Page 58: ...spended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane Arm The horizontal distance from the reference datum to the center of gravity C G of an item Basic Empty Weight The weight of an empty airplane including full engine oil and unusable fuel This equals empty weight plus the weight of unusable fuel and the weight of all the engine o...

Page 59: ... an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number of digits Payload Weight of occupants cargo and baggage Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes Empty Weight The weight of an empty airplane before any oil or fuel has been added This includes all perma...

Page 60: ...rea Navigation SBAS Satellite Based Augmentation System equivalent to WAAS in the United States TAWS Terrain Awareness and Warning System VNAV or VNV Vertical Navigation WAAS Wide Area Augmentation System Tare The weight of chocks blocks stands etc used on the scales when weighing an airplane Unusable Fuel Fuel that is not available for flight planning Useful Load Difference between Ramp Weight an...

Page 61: ... Engine Airframe Unit GIA Garmin Integrated Avionics Unit GDL Garmin Data Link GMA Garmin Audio Panel GMU Garmin Magnetometer Unit GRS Garmin Attitude and Heading Reference System GSA Garmin Autopilot Servo GSM Garmin Autopilot Servo Mount GTX Garmin Transponder GWX Garmin Airborne Weather Radar May 2015 ...

Page 62: ...General Model G58 Section 1 1 26 THIS PAGE INTENTIONALLY LEFT BLANK May 2015 ...

Page 63: ...ine Type 2 7 Engine Operating Limitations 2 7 Fuel Limits 2 8 Approved Engine Fuels 2 8 Fuel Capacity 2 8 Standard Fuel System 2 8 Optional Fuel System 2 8 Fuel Management 2 8 Oil Specification 2 8 Number of Propellers 2 9 Propeller Manufacturer 2 9 Number of Blades 2 9 Propeller Type 2 9 Propeller Diameter 2 9 Power Plant Instrument Markings 2 10 Manifold Pressure 2 10 Tachometer 2 10 Fuel Flow 2...

Page 64: ...2 Fuel Quantity 2 12 Deice Pressure Gage 2 12 Propeller Deice Ammeter 2 13 Weight Limits 2 13 Center of Gravity Landing Gear Extended 2 13 Reference Datum 2 13 Mean Aerodynamic Chord 2 13 Maneuver Limits 2 14 Flight Load Factors 5500 Pounds 2 14 Minimum Flight Crew 2 14 Maximum Passenger Seating Configuration 2 14 Seating 2 14 Icing Limitations 2 14 Limitations When Encountering Severe Icing Condi...

Page 65: ...ystem 2 17 GPS Navigation 2 23 Garmin GFC 700 Autopilot System Autopilot Flight Director Electric Trim 2 26 L 3 Communications SKYWATCH SKY497 Traffic Advisory System if installed 2 27 Weather Radar 2 27 Garmin Terrain Awareness and Warning System TAWS 2 28 Placards Markings 2 29 Kinds Of Operations 2 41 Kinds Of Operations Equipment List 2 41 ...

Page 66: ...Model G58 2 4 May 2015 Section 2 THIS PAGE INTENTIONALLY LEFT BLANK Limitations ...

Page 67: ...nd then only with caution Maneuvering VA 156 156 Do not make full or abrupt control movements above this speed Maximum Flap Extension Extended VFE Approach 15 Full Down 30 152 122 152 122 Do not extend flaps or operate with flaps extended above this speed Maximum Landing Gear Operating Extended VLO VLE 152 152 Do not extend retract or operate with gear extended above this speed Single Engine Minim...

Page 68: ... CODED SPEED RANGE STRIP OR MARKING KIAS RANGE SIGNIFICANCE White Strip 74 122 Full Flap Operating Range Lower Limit Stall speed with flaps down at maximum weight Upper Limit Maximum speed permissible with flaps fully extended White Triangle 152 Maximum Speed for approach flaps Blue Strip 101 Single Engine Best Rate of Climb Speed Red Strip 84 Minimum Single Engine Control VMCA Green Strip 84 195 ...

Page 69: ...ER Teledyne Continental Motors Inc Mobile Alabama ENGINE MODEL NUMBER IO 550 C ENGINE TYPE Normally aspirated fuel injected direct drive air cooled six cylinder horizontally opposed 550 cubic inch displacement 300 H P ENGINE OPERATING LIMITATIONS Take off and Maximum Continuous Power Full Throttle 2700 RPM Maximum Cylinder Head Temperature 238 C Maximum Oil Temperature 116 C Minimum Take off Oil T...

Page 70: ...quantity display indicates in the yellow band or with less than 13 gallons in each wing fuel system The fuel crossfeed system to be used during emergency con ditions in level flight only Maximum slip duration 30 seconds OIL SPECIFICATION Use MIL L 22851 Ashless Dispersant Oils meeting the require ments of the latest revision of Teledyne Continental Motors Corporation Specification MHS 24B or curre...

Page 71: ...opeller using a 3AF32C512 X hub with X 82NEA 5 blades NOTE The letters appearing in the place of the X represent minor variations in the propeller hub or blades They do not affect eligibility or interchangeability Hartzell propellers Optional Constant speed variable pitch three blade propeller using a PHC J3YF 2UF hub with FC7391D K blades PROPELLER DIAMETER McCauley Propellers Max 77 inches Min 7...

Page 72: ...t will change color to yellow or red if the engine parameter is operating in a caution or prohib ited range If the engine parameter is operating in the prohib ited range the pointer digits and placard will flash MANIFOLD PRESSURE Operating Range Green Arc 15 0 to 29 6 in Hg TACHOMETER Operating Range Green Arc 1800 to 2700 RPM Prohibited Range Red Arc 2700 to 3000 RPM Overspeed Indications 2701 RP...

Page 73: ...b fuel flows for only two power set tings 2700 RPM and Full Throttle 2500 RPM and Full Throttle CYLINDER HEAD TEMPERATURE The number displayed in the pointer indicates the hottest cylin der Operating Range Green Bar 116 to 238 C Prohibited Range Red Bar 238 to 250 C OIL TEMPERATURE If engine is operating below 500 RPM oil temperatures in the yellow bar will not cause the pointer or digits to chang...

Page 74: ...nters placarded L and R indicate the load of each alternator 100 load on left alternator 100 amps 100 load on right alternator 100 amps Operating Range Green Bar 0 to 100 Caution Range Yellow Bar Yellow Digits 100 to 110 BUS VOLTAGE Caution Range 10 to 24 volts Operating Range 24 to 30 volts Caution Range 30 to 33 volts FUEL QUANTITY Two pointers placarded L and R indicate the fuel quantity in eac...

Page 75: ...fer to Section 6 WEIGHT AND BALANCE EQUIPMENT LIST for additional information CENTER OF GRAVITY LANDING GEAR EXTENDED Forward Limits 74 0 inches aft of datum at 4200 lbs and under then straight line variation to 78 0 inches aft of datum at gross weight of 5400 lbs maximum landing weight and 78 3 inches aft of datum at gross weight of 5500 lbs Aft Limit 86 inches aft of datum at all weights REFEREN...

Page 76: ...eat back of an occupied pilot s or copilot s seat in the full back position The seat back of an occupied optional copilot s full reclining seat and the seat backs of all other occupied seats must be in the most upright position for takeoffs and landings Occupied aft facing seats must have headrests fully extended ICING LIMITATIONS Minimum Airspeed During Icing Conditions 130 knots Minimum Ambient ...

Page 77: ...the capability of the ice protection system or may result in ice forming aft of the protected surfaces This ice may not be shed using the ice pro tection systems and may seriously degrade the performance and controllability of the airplane 1 During flight severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues If one or more...

Page 78: ...hts must be operative prior to flight into known or forecast icing conditions at night NOTE This supersedes any relief provided by the Mas ter Minimum Equipment List MMEL AVIONICS GENERAL 1 The appropriate Garmin G1000 Cockpit Reference Guide for the Beechcraft Baron 58 G58 must be imme diately available to the flight crew 2 The L 3 Communications SkyWatch Traffic Advisory System Model SKY497 Traf...

Page 79: ... each version of software are listed on the following pages The following methods may be used to determine the level of software installed on the airplane a Refer to the MFD upon initial power up The Splash Screen will display the current system software ver sion at the top of the page e g Beechcraft 58 G58 System 0857 05 b Select the SYSTEM STATUS page of the AUX Group on the MFD The current soft...

Page 80: ...BBREVIATION SOFTWARE VERSION Primary Flight Display PFD1 6 00 Multifunction Display MFD1 6 00 Audio Control Panel Marker Beacon System GMA1 2 07 Attitude and Heading Reference System AHRS GRS1 2 03 Air Data Computer ADC GDC1 2 05 Integrated Avionics Unit GIA1 GIA2 4 00 Engine Airframe Unit L R GEA1 GEA2 2 06 Global Positioning System GPS1 GPS2 3 01 Autopilot GSA PTCH CTL GSA PTCH MON GSA PTCH TRIM...

Page 81: ...2 07 Attitude and Heading Reference System AHRS GRS1 2 03 Air Data Computer ADC GDC1 2 05 Integrated Avionics Unit GIA1 GIA2 4 00 Engine Airframe Unit L R GEA1 GEA2 2 06 Global Positioning System GPS1 GPS2 3 01 Autopilot GSA PTCH CTL GSA PTCH MON GSA PTCH TRIM C GSA PTCH TRIM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW MON 2 08 Data Link GDL 69 3 00 00 Mode S Transponder GTX1 4 02 Airborne Wea...

Page 82: ...3 03 Attitude and Heading Reference System AHRS GRS1 2 11 Air Data Computer ADC GDC1 3 01 Integrated Avionics Unit GIA1 GIA2 5 40 Engine Airframe Unit L R GEA1 GEA2 2 07 Global Positioning System GPS1 GPS2 3 0 Autopilot GSA PTCH CTL GSA PTCH MON GSA PTCH TRIM C GSA PTCH TRIM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW MON 2 13 Data Link GDL 69 3 20 00 Mode S Transponder GTX1 4 06 Airborne Weat...

Page 83: ...ultifunction Display MFD1 8 10 Audio Control Panel Marker Beacon System GMA1 4 02 Attitude and Heading Reference System AHRS GRS1 2 11 Air Data Computer ADC GDC1 3 01 Integrated Avionics Unit GIA1 GIA2 5 40 Engine Airframe Unit L R GEA1 GEA2 2 07 Global Positioning System GPS1 GPS2 3 0 Autopilot GSA PTCH CTL GSA PTCH MON GSA PTCH TRIM C GSA PTCH TRIM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW...

Page 84: ...POSITION HDDD MM MM Latitude and longitude will be entered in degrees minutes and decimal minutes i e 45 30 30 would be entered as 45 30 5 minutes Map Datum WGS 84 The G1000 will use the WGS 84 Datum In some areas outside the United States datums other than WGS 84 may be used If the G1000 is authorized for use by the appropriate Airworthiness Authority the required geodetic datum must be set in th...

Page 85: ...g arrival or departure procedure Failing to observe this limitation can cause deviation indications loss of GPS navigation information and other display anomalies If display anomalies are noted after editing the flight plan perform either a direct to or activate leg operation as appropriate on the flight plan to ensure correct flight plan sequencing and guidance GPS NAVIGATION 1 Navigation is base...

Page 86: ... non precision instrument approach opera tions within the U S National Airspace System in accordance with AC 20 138A including GPS or GPS and RNAV GPS approaches c VFR IFR operations on Standard Instrument Depar tures SIDs RNAV 1 and Standard Instrument Arrivals STARs RNAV 1 in accordance with AC 90 100 d VFR IFR Oceanic and Remote operations in accor dance with Appendix 1 of AC 20 138A A Garmin P...

Page 87: ...AWS N A 3 Navigation must not be predicated upon the use of the TAWS display The TAWS display is intended to serve as a situational awareness tool only and may not pro vide the accuracy and or fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions 4 The GPS ALT displayed on the MFD is a calculated value and must not be considered as a primary source of altitude or use...

Page 88: ...Model G58 Baron P N 58 590000 67TC2 4 of 4 information for primary terrain avoidance TAWS is intended only to enhance situational awareness May 2008 ...

Page 89: ... required by the applicable operating rules it must be served by an approach based on other than GPS navigation the airplane must have the operational equipment capable of using that naviga tion aid and the required navigation aid must be opera tional 9 Airplanes equipped with Airframe System Software Ver sion 0857 05 or 0857 06 are approved for approach pro cedures with vertical guidance includin...

Page 90: ... shoulder harness fas tened 3 The autopilot and yaw damper must be off for takeoff and landing 4 The autopilot minimum engagement heights are After Takeoff 400 feet During Cruise 1000 feet During precision and non precision approaches 200 feet 5 Autopilot operations with the G1000 intentionally placed in the reversionary mode either the PFD or MFD inoper ative is limited to VFR training operations...

Page 91: ...SORY SYSTEM if installed 1 The pilot must not maneuver the airplane based only on the traffic display The traffic display is intended to assist in visually locating traffic and lacks the resolution neces sary for use in evasive maneuvering 2 If the pilot is advised by Air Traffic Control to disable the altitude reporting function of the transponder the Traffic Advisory System must be placed in Sta...

Page 92: ...n information around airports to prevent nuisance alerts 2 Terrain data is not displayed when the airplane latitude is greater than 75 degrees North or 60 degrees South This will be annunciated as TAWS N A 3 Navigation must not be predicated upon the use of the TAWS display The TAWS Display is intended to serve as a situational awareness tool only and may not pro vide the accuracy and or fidelity ...

Page 93: ...d Post If Electrothermal Heated Windshield Segment is Installed On Left Sidewall TH00C 020329AA AI TURN STROBE LIGHTS OFF WHEN TAXING IN VICINITY OF OTHER AIRCRAFT OR WHEN FLYING IN FOG OR CLOUDS STANDARD POSITION LIGHTS TO BE USED FOR ALL NIGHT OPERATIONS MAX STRUCTURAL CRUISE SPEED 195 KTS NEVER EXCEED SPEED 223 KTS MIN CONTROL SPEED SINGLE ENGINE 84 KTS MAX DESIGN MANEUVER SPEED 156 KTS MAX FLA...

Page 94: ...e MFD On Upper Left Side Panel Airplanes Approved for Flight In Icing Conditions On Upper Left Side Panel Airplanes Not Approved for Flight In Icing Conditions On Upper Right Side of Instrument Panel TH 2173 and After E 02C 051578AA AI TH02C 063324AA AI May 2015 ...

Page 95: ...TIONAL 166 GALLON CAPACITY FUEL SYSTEM Between Fuel Selector Handles F F 0 F F 0 FUEL SELECTOR CROSS FEED IN LEVEL FLIGHT ONLY USE CROSS FEED LEFT WING 97 GAL ON RIGHT WING 97 GAL ON TH00C 020331AA AI DO NOT TAKE OFF IF FUEL QUANTITY GAGES INDICATE IN YELLOW ARC OR WITH LESS THAN 13 GALLONS IN EACH WING SYSTEM May 2015 ...

Page 96: ...Seat Backs for 3rd and 4th Seats On Top of Front Spar Carry Thru Structure Between Front Seats TH02C 000396AA AI EMERGENCY LANDING GEAR INSTRUCTIONS TO EXTEND ENGAGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISE AS FAR AS POSSIBLE 50 TURNS May 2015 ...

Page 97: ...Limitations Section 2 Model G58 2 33 On Emergency Crank Access Cover Adjacent To Cabin Door Handle On Inside of Cabin Door Adjacent to Door Handle May 2015 ...

Page 98: ...l Adjacent to Pilot Adjacent to Openable Cabin Window Handles TH02C 060621AA AI WARNING EMERGENCY AIRSPEED STATIC SOURCE SEE PILOTS CHECK LIST OR FLIGHT MANUAL ON EMERGENCY OFF NORMAL EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER CALIBRATION ERROR May 2015 ...

Page 99: ...Limitations Section 2 Model G58 2 35 On Face of Emergency Exit Latch Cover On Emergency Exit Handle On Openable Cabin Windows On Window Adjacent to Pilot s Seat May 2015 ...

Page 100: ...t to Copilot s Seat On Windows Adjacent to 5th and 6th Seats and 3rd 4th For ward Facing Seats On Windows Adjacent to 3rd 4th Aft Facing Club Seats On Inside of Utility Door on Left Sidewall of Utility Compart ment or on Aft Bulkhead C95TH02C0160 May 2015 ...

Page 101: ...Aft Bulkhead with utility door removal kit On Panel When Utility Doors are Removed In Plain View When Nose Baggage Compartment Door is Open On Left Side of Instrument Panel if Air Conditioner installed C95TH02C0161 E 02C 060731AA AI AIR COND SYS MUST BE OFF BEFORE TAKEOFF May 2015 ...

Page 102: ...djacent to Oil Filler Caps Adjacent to Fuel Filler Caps TH02D 082106AA AI TH02D 082107AA AI AVGAS ONLY GRADE 100LL 100 GRADE FOR ALTERNATE FUELS SEE PILOTS OPERATING HANDBOOK CAUTION DO NOT INSERT FUEL NOZZLE MORE THAN 3 INTO TANK May 2015 ...

Page 103: ...ction 2 Model G58 2 39 For Standard 194 Gallon Capacity Fuel System Adjacent to Fuel Filler Caps For Optional 166 Gallon Capacity Fuel System Adjacent to Fuel Filler Caps TH02D 082105AA AI TH02D 082103AA AI May 2015 ...

Page 104: ...Limitations Model G58 Section 2 2 40 On External Power Compartment Door TH02D 082104AA AI May 2015 ...

Page 105: ... predicated The systems and equipment listed must be installed and operable for the particular kind of operation indi cated unless 1 The airplane is approved to be operated in accordance with a current Minimum Equipment List MEL issued by the FAA or 2 An alternate procedure is provided in the Pilot s Operat ing Handbook and FAA Approved Airplane Flight Manual for the inoperative state of the liste...

Page 106: ...KPIT DISPLAY SYSTEM Primary Flight Display PFD 1 1 1 1 1 Multifunction Display MFD 0 1 1 1 1 Integrated Avionics Unit GIA 1 1 2 2 2 Attitude Heading Unit AHRS 0 1 1 1 1 Engine Airframe Unit GEA 2 2 2 2 2 Air Data Computer ADC 1 1 1 1 1 Audio Panel GMA 0 0 1 1 1 OAT 1 1 1 1 1 STANDBY INSTRUMENTS Airspeed Indicator 1 1 1 1 1 Attitude Indicator 1 1 1 1 1 Altimeter 1 1 1 1 1 Magnetic Compass 1 1 1 1 1...

Page 107: ...tion Indicator Lights 3 3 3 3 3 Stall Warning System 1 1 1 1 1 FUEL Electrically Driven Boost Pump 2 2 2 2 2 Engine Driven Boost Pump 2 2 2 2 2 Fuel Selector Valve 2 2 2 2 2 ICE AND RAIN PROTECTION Emergency Static Air System 0 0 1 1 1 Fuel Vent Heater 0 0 2 2 2 Pitot Heater 0 0 1 1 1 Propeller Deice System 0 0 0 0 1 Electrothermal Heated Windshield Segment 0 0 0 0 1 Surface Deice System Inboard a...

Page 108: ...Lights 4 4 4 4 4 Landing Gear Motor and Gearbox 1 1 1 1 1 Landing Gear Warning Horn 1 1 1 1 1 LIGHTS Cockpit and Display Lighting System 0 1 1 1 1 Landing Light 0 1 0 1 1 Navigation Lights 0 3 0 3 3 Flashing Beacon Vert Stab 0 1 0 1 1 RESTRAINT SYSTEM Seat Belt per seat 1 1 1 1 1 Shoulder Harness per seat 1 1 1 1 1 Shoulder Harness crew compartment 1 1 1 1 1 Right side may be inoperative provided ...

Page 109: ...Lift off and in Flight 3 6 Engine Fire 3 7 On The Ground 3 7 In Flight 3 7 Emergency Descent 3 8 Glide 3 8 Landing Emergencies 3 9 Gear Up Landing 3 9 Systems Emergencies 3 10 One Engine Inoperative Operation on Crossfeed 3 10 Electrical Smoke or Fire 3 11 Alternator Failure L ALT INOP or R ALT INOP 3 12 Electrical Systems Load Shedding 3 13 Avionics 3 14 Autopilot Failures 3 14 Autopilot Malfunct...

Page 110: ...FD 3 20 Emergency Communications 3 20 Garmin Terrain Awareness and Warning System TAWS 3 20 TAWS Forward Looking Terrain Warning PULL UP 3 20 Excessive Descent Rate Warning PULL UP 3 23 Additional Warning Annunciations 3 24 Fuel Flow High FUEL FLOW HI 3 24 Cylinder Head Temperature High CHT HI 3 25 Oil Temperature High OIL TEMP HI 3 25 Oil Pressure High OIL PRESS HI 3 26 Oil Pressure Low OIL PRESS...

Page 111: ...E The following information is presented to enable the pilot to form in advance a defi nite plan of action for coping with the most probable emergency situations which could occur in the operation of the airplane In order to supply one safe speed for each type of emergency situation the airspeeds presented were derived at 5500 lbs 5400 lbs for landing Immediate action procedures are delin eated by...

Page 112: ...al Approach Flaps Down 30 95 kts Intentional One Engine Inoperative Speed VSSE 88 kts Maximum Range Glide 115 kts The stall warning horn is inoperative when the battery and alternator switches are turned off ONE ENGINE INOPERATIVE PROCEDURES CONTROLLABILITY VS AIRSPEED Airspeed is the single most important factor in maintaining air plane control during single engine operations The airplane can be ...

Page 113: ...tive engine 2 THROTTLE Partially retard the throttle for the engine that is believed to be inoperative there should be no change in control pressures or in the sound of the engine if the correct throttle has been selected AT LOW ALTI TUDE AND AIRSPEED THIS CHECK MUST BE ACCOMPLISHED WITH EXTREME CAUTION Do not attempt to determine the inoperative engine by means of the tachometers or the manifold ...

Page 114: ...P 2 Throttle inoperative engine CLOSED 3 Propeller inoperative engine FEATHER 4 Power operative engine AS REQUIRED 5 Airspeed MAINTAIN SPEED AT ENGINE FAILURE 101 kts MAX UNTIL OBSTACLES ARE CLEARED NOTE The most important aspect of engine failure is the necessity to maintain lateral and directional control If airspeed is below VMCA 84 kts reduce power on the opera tive engine as required to maint...

Page 115: ...ternator k Cowl Flap CLOSED ENGINE FIRE ON THE GROUND 1 Mixture Controls CUT OFF 2 Starter affected engine CONTINUE TO CRANK 3 Fuel Selector Valves OFF 4 Magnetos OFF 5 Alternators OFF 6 Batteries OFF 7 Exit airplane and move to a safe distance IN FLIGHT Shut down the affected engine according to the following pro cedure and land immediately Follow the applicable one engine inoperative procedures ...

Page 116: ... Gear DOWN 5 Flaps APPROACH 15 GLIDE 1 Propellers FEATHERED 2 Flaps UP 0 3 Landing Gear UP NOTE The landing gear will not retract unless one of the throttles is in a position correspond ing to approximately 15 in Hg manifold pressure or above 4 Airspeed 115 KTS 5 Glide Ratio 2 nautical miles for each 1000 feet of altitude April 2008 ...

Page 117: ... choose firm sod When assured of reaching landing site 1 Cowl Flaps CLOSED 2 Wing Flaps AS DESIRED 3 Throttles CLOSED 4 Fuel Selectors OFF 5 Mixture Controls CUT OFF 6 Magnetos OFF 7 Alternators OFF 8 Batteries OFF 9 Wings KEEP LEVEL DURING TOUCHDOWN 10 Get clear of the airplane as soon as possible after it stops NOTE The gear up landing procedures are based on the best available information and n...

Page 118: ... flight only Left Engine Inoperative 1 Right Fuel Boost Pump LOW 2 Left Fuel Selector OFF 3 Right Fuel Selector CROSSFEED feel for detent confirm visually 4 Right Fuel Boost Pump LOW or OFF as required Right Engine Inoperative 1 Left Fuel Boost Pump LOW 2 Right Fuel Selector OFF 3 Left Fuel Selector CROSSFEED feel for detent confirm visually 4 Left Fuel Boost Pump LOW or OFF as required April 2008...

Page 119: ...ernators off Only the standby instru ments will be available 4 All Electrical Switches OFF 5 Dissipation of smoke may be aided by the following a Cabin Air and Cabin Heat Controls FULL FORWARD b Pilot Air and Copilot Air PULL OPEN c Overhead Fresh Air Outlets OPEN If smoke or fire ceases individually restore electrical equip ment to isolate defective equipment 6 Batteries ON 7 Alternators ON 8 Ess...

Page 120: ...ENTARILY THEN ON If the warning alert extinguishes and a positive load is indi cated 4 Continue to use the alternator If the warning alert remains displayed 5 Alternator failed side OFF 6 Nonessential Electrical Equipment OFF AS REQUIRED to reduce load on operative alternator 7 Alternator failed side BUS TIE ties the side with the functional alternator to inoperative side 8 ALT LOAD MONITOR 9 None...

Page 121: ...cy operating time 30 minutes minimum per battery is based on the following loads being shed 1 Left and Right Alternators OFF 2 Avionics Master OFF 3 Prop Sync OFF 4 Fuel Vent Heat OFF 5 Stall Warning Heat OFF 6 Propeller Deice OFF 7 Windshield Anti Ice OFF 8 Air Conditioner Blower if installed OFF 9 Heater Blower OFF 10 Strobe Lights OFF 11 Beacon OFF 12 Nav LIghts OFF 13 Flood Lights AS REQUIRED ...

Page 122: ...pilot can be manually disengaged by 1 Pressing the red AP DISC switch on the pilot s control wheel Also disconnects the Yaw Damper 2 Moving the left outboard side of the electric trim switch Yaw Damper will not disengage 3 Pressing the AP key on the MFD Yaw Damper will not disengage 4 Pressing the GO AROUND switch on the left side of the Throttle Yaw Damper will not disengage The autopilot can als...

Page 123: ...ITCH and or ROLL to indicate axis failed Loss of the following items will cause the autopilot to automati cally disconnect The autopilot will remain inoperative and can not be re engaged until the inoperative item is restored AHRS ADC PFD GIA 1 INTEG AVION 1 and GIA 2 INTEG AVION 2 1 AP DISC Switch PRESS to cancel tone and flashing AP or 2 Left outboard Side of Trim Switch ACTUATE to cancel tone a...

Page 124: ...AS REQUIRED 2 Autopilot a Disconnect and manually slow the airplane or b Use VS or PIT Mode and NOSE UP key to slow the airplane 3 MAXSPD EXTINGUISHED when speed is reduced below approx 205 KIAS If in PIT mode the flight director will revert to the original pitch attitude when the MAX SPD is cancelled if the pitch attitude is not adjusted with the NOSE UP key 4 Autopilot Overspeed Recovery is not ...

Page 125: ...rol Wheel HOLD FIRMLY 2 Standby Attitude Indicator CROSS CHECK FOR PROPER ATTITUDE 3 AP DISC Switch PRESS AND HOLD 4 Pitch Trim RETRIM IF REQD 5 AP DISC Switch RELEASE If uncommanded deviation occurs again 6 AP DISC Switch PRESS AND HOLD 7 AP SERVOS Circuit Breaker PULL 8 AP DISC Switch RELEASE 9 Pitch Trim RETRIM IF REQD ELECTRIC PITCH TRIM FAILURE PTRM Illumination of the red PTRM annunciator on...

Page 126: ...nated may cause a PTRM fault UNSCHEDULED ELECTRIC PITCH TRIM Red Flashing PTRM Possible yellow ELE or ELE 1 Airplane Attitude MAINTAIN USING ELEVATOR CONTROL expect residual pitch forces 2 AP DISC Switch DEPRESS AND HOLD to interrupt the pitch trim 3 Avionics Switch OFF 4 AP DISC Switch RELEASE 5 AP SERVOS Circuit Breaker PULL 6 Avionics Switch ON 7 Pitch Trim RETRIM AS REQD NOTE Autopilot will no...

Page 127: ...llow HDG with red X Compass Rose Digits Removed Course Pointer will indicate straight up Autopilot and Yaw Damper will Disengage 1 AP DISC Switch PRESS if required to cancel autopilot tone flashing AP 2 Use Standby Attitude Indicator and Magnetic compass 3 Nav Course SET USING DIGITAL WINDOW 4 Land as soon as practical FAILURE OF PFD OR MFD If the remaining display does not automatically revert to...

Page 128: ...uency will be available to the pilot through the headset GARMIN TERRAIN AWARENESS AND WARNING SYSTEM TAWS TH 2138 TH 2141 and after and prior airplanes in compli ance with Service Bulletin 34 3774 TAWS FORWARD LOOKING TERRAIN WARNING PULL UP Voice Warning Alert See the following table Reduced Required Terrain or Obstacle Clearance RTC or ROC Warning Voice warning alerts and annunciators are provid...

Page 129: ...ight corner of the MFD displaying an appropriate annunciator See Section 7 SYSTEMS DESCRIPTION NOTE Pilots are authorized to deviate from their current air traffic control ATC clearance to the extent necessary to comply with a TAWS warning REASON VOICE WARNING ALERT Violation of Required Terrain Clearance RTC Requirements within 30 seconds Terrain Terrain Pull Up Pull Up Imminent Terrain Impact IT...

Page 130: ...Retracted 5 Continue climb at 92 KIAS until terrain clearance is assured The voice warning alert will be repeated until the threat no longer exists 6 Advise Air Traffic Control as necessary Only vertical maneuvers are recommended unless the pilot using all available informa tion and instruments determines that a turn in addition to the vertical escape maneuver is the safest course of action In Day...

Page 131: ... warn ing will be provided whether or not the TAWS system is inhib ited A red PULL UP will be displayed on the PFD and the MFD TAWS page if selected and the PULL UP voice warn ing alert will be heard If the TAWS page is not selected a red PULL UP will be displayed in a pop up window on the Map page This warning will normally be preceded by a caution See Section 3A ABNORMAL PROCEDURES The following...

Page 132: ...evert to the default ENGINE page display Hence the following warning annunciations are not required Other software versions require the pilot to manually select the ENGINE page display and necessitate additional warning annunciations It remains the pilot s responsibility to monitor and operate the airplane within the speci fied limits 2 ENGINE softkey PRESS As required to return to primary engine ...

Page 133: ...GINE FAILURE AFTER LIFT OFF AND IN FLIGHT procedures to secure affected engine or 8 Land at nearest suitable airport using the minimum power required OIL TEMPERATURE HIGH OIL TEMP HI 1 Oil Temperature CONFIRM 116 C 2 Cowl Flaps OPEN 3 Power REDUCE TO LOWEST PRACTICAL 4 Oil Pressure CHECK If oil temperature stabilizes below 116 C and annunciation extinguishes 5 Continue flight to destination at pil...

Page 134: ... IN FLIGHT procedures to secure affected engine or 3 Land at the nearest suitable airport using the minimum power required FUEL QUANTITY LOW FUEL QTY LO 1 Fuel Indicators CONFIRM LO QTY and TANK 2 Land at nearest suitable airport EMERGENCY EXITS The openable windows on the left and right side of the cabin may be used for emergency egress in addition to the cabin door and utility doors An emergency...

Page 135: ...d handle located on lower inboard side of seat back 2 Fold seat back over SPINS Intentional spins are prohibited If an unintentional spin is encountered perform the following procedure IMMEDIATELY THE LONGER THE DELAY THE MORE DIFFICULT RECOVERY WILL BECOME Steps 1 through 3 should be done AGGRESSIVELY and SIMULTANEOUSLY The full for ward position of the control column may be reduced slightly if r...

Page 136: ...ING THE SEVERE ICING ENVIRONMENT These procedures are applicable to all flight phases from take off to landing Monitor the ambient air temperature While severe icing may form at temperatures as cold as 18 C increased vigilance is warranted at temperatures around freez ing with visible moisture present If the visual cues specified in Section 2 LIMITATIONS for identifying severe icing conditions are...

Page 137: ...ved reduce the angle of attack 6 Do not extend flaps when holding in icing conditions Operation with flaps extended can result in a reduced wing angle of attack with the possibility of ice forming on the upper surface further aft on the wing than normal possibly aft of the protected area 7 If the flaps are extended do not retract them until the air frame is clear of ice 8 Report these weather cond...

Page 138: ...Emergency Procedures Model G58 Section 3 3 30 THIS PAGE INTENTIONALLY LEFT BLANK April 2008 ...

Page 139: ...eaker Tripped 3A 8 Landing Gear Manual Extension 3A 8 Landing Gear Retraction After Practice Manual Extension 3A 9 Ice Protection 3A 10 Surface Deice System 3A 10 Electrothermal Propeller Deice System 3A 11 Emergency Static Air Source System 3A 12 Electrothermal Heated Windshield Segment 3A 12 Heated Pitot Tube 3A 13 Forward Cabin Door Open in Flight 3A 13 Avionics 3A 14 Autopilot Failures 3A 14 F...

Page 140: ... Signal 3A 19 Position Error POSN ERROR 3A 19 Failure of Remote Autonomous Integrity Monitoring RAIM 3A 19 Garmin Terrain Awareness and Warning System TAWS 3A 20 TAWS Forward Looking Caution TERRAIN 3A 20 Excessive Descent Rate Caution TERRAIN 3A 21 Negative Climb Rate After Takeoff TERRAIN 3A 22 Premature Descent During An Approach TERRAIN 3A 23 Ditching Off Airport Landing or Flying VFR Around U...

Page 141: ...ely 1 4 travel 4 Mixture Control FULL RICH below 5000 ft 1 2 travel above 5000 ft 5 Fuel Boost Pump LOW 6 Magnetos ON 7 Propellers With Unfeathering Accumulators a Propeller Control FORWARD OF FEATHERING DETENT until engine obtains 600 RPM b Propeller Control BACK TO DETENT to avoid overspeeding c Starter if necessary ENGAGE MOMENTARILY to accomplish unfeathering d If propeller does not unfeather ...

Page 142: ...able power has been regained 10 Alternator ON 11 Oil Pressure CHECK 12 Warm Up Engine approximately 1500 RPM and 15 in Hg 13 Power AS REQUIRED 14 Trim AS REQUIRED LANDING EMERGENCIES ONE ENGINE INOPERATIVE LANDING On final approach and when it is certain that the field can be reached 1 Landing Gear DOWN 2 Flaps APPROACH 15 3 Airspeed 107 KTS 4 Power AS REQUIRED to maintain 800 ft min rate of desce...

Page 143: ...ght might not be possible for certain combinations of weight temperature and altitude In any event DO NOT attempt a one engine inoperative go around after flaps have been fully extended 1 Power MAXIMUM ALLOWABLE 2 Landing Gear UP 3 Flaps UP 0 4 Airspeed MAINTAIN 101 KTS MINIMUM April 2008 ...

Page 144: ... OFF 2 Batteries OFF 3 DO NOT TAKE OFF Illuminated In Flight After Air Start 1 Alternator affected engine OFF 2 Battery affected engine OFF NOTE Depending on which Bus is affected head ing and attitude information will be lost Use standby instruments 3 Land as soon as practical ALTERNATOR HIGH VOLTAGE LBUS VOLT HI or RBUS VOLT HI Display of either LBUS VOLT HI or RBUS VOLT HI caution alert on the ...

Page 145: ...lectrical Equipment ON AS REQUIRED maintain load limits of operative alternator ALTERNATOR LOW VOLTAGE LBUS VOLT LO or RBUS VOLT LO Display of either LBUS VOLT LO or RBUS VOLT LO caution alert on the PFD 1 MFD Softkeys SELECT ENGINE AND SYSTEM 2 Bus Volts failed side CHECK If voltage is greater than 24 volts a false warning is indicated 3 Continue to use the alternator If voltage is less than 24 v...

Page 146: ... for continued safe flight a Circuit Breaker after allowing to cool for a minimum of 10 sec PUSH TO RESET If Circuit Breaker Trips Again b Circuit Breaker DO NOT RESET LANDING GEAR MANUAL EXTENSION 1 Airspeed 152 KTS or LESS NOTE Manual extension of the gear can be facili tated by first reducing the airspeed as much as practical 2 LANDING GEAR MOTOR Circuit Breaker left circuit breaker panel PULL ...

Page 147: ...AR MOTOR Circuit Breaker 9 The landing gear should be considered UNLOCKED until the airplane is on jacks and the system has been cycled and checked Do not operate the landing gear electrically with the handcrank engaged Damage to the mechanism could occur The manual extension system is designed to lower the landing gear only DO NOT ATTEMPT TO RETRACT THE GEAR MANUALLY LANDING GEAR RETRACTION AFTER...

Page 148: ... boots will inflate only as long as the switch is held in the MAN manual position When the switch is released the boots will deflate Failure of boots to deflate 1 Pull Surface Deice Circuit Breaker on pilot s sidewall cir cuit breaker panel 2 If boots reinflate after Surface Deice Circuit Breaker is reset use circuit breaker as a manual surface deice switch following the procedures outlined in Fai...

Page 149: ...rative 2 Zero to 14 Amps If the propeller deice system ammeter occasionally or reg ularly indicates less than 14 amps operation of the propel ler deice system can continue unless serious propeller imbalance results from irregular ice shedding 3 18 to 23 Amps If the propeller deice system ammeter occasionally or reg ularly indicates 18 to 23 amps operation of the propeller deice system can continue...

Page 150: ...hanges beyond normal calibration differ ences Whenever any obstruction exists in the Normal Static Air Sys tem or the Emergency Static Air System is desired for use 1 Emergency Static Air Source EMERGENCY ON lower sidewall adjacent to pilot 2 For Airspeed Calibration and Altimeter Correction refer to Section 5 PERFORMANCE When the Emergency Static Air System is no longer needed 3 Emergency Static ...

Page 151: ...AS POSSIBLE WING ICE LIGHT Failure of the Wing Ice Light at night in icing conditions 1 Cabin Lights Circuit Breaker CHECK 2 Icing Conditions EXIT AS SOON AS POSSIBLE FORWARD CABIN DOOR OPEN IN FLIGHT If the forward cabin door is not properly latched it may open during takeoff roll or during flight The door may trail open approximately 3 inches but the flight characteristics of the air plane will ...

Page 152: ...OT OUT OF TRIM Yellow RUD RUD AIL AIL ELE or ELE Do not attempt to overpower the autopilot in the event of a mistrim The autopilot servos will oppose pilot input and in the case of the pitch axis will trim the elevator in the opposite direction to the pilot input This could lead to a significant out of trim condi tion If AIL or AIL is illuminated 1 Slip Skid Indicator VERIFY CENTER 2 Fuel Imbalanc...

Page 153: ...TH 2158 not in compliance with S B 22 3795 Description of Change Uncommanded pulsing of the control column during overly aggressive autopilot captures and during use of the PIT mode affects and ABNORMAL and NORMAL PROCEDURES Sections Filing Instructions Insert the following pages of this temporary change into the Model G58 Pilot s Operating Handbook and FAA Approved Airplane Flight Manual and reta...

Page 154: ...000 67TC1 Rev 1 June 2006 2 of 4 ABNORMAL PROCEDURES AVIONICS AUTOPILOT FAILURES NUISANCE PITCH PULSE If a nuisance pitch pulse is encountered disconnect autopilot Retrim and stabilize airplane in the desired flight path and re engage the autopilot if desired ...

Page 155: ...the default mode ROL or PIT Loss of Selected Vertical Mode FLC VS ALT GS or Loss of Selected Lateral Mode HDG VOR GPS BC LOC VAPP LOC 1 Autopilot Mode Control SELECT ANOTHER VERTICAL OR LATERAL MODE If on an Instrument Approach 2 Autopilot if coupled Flight Director DISCONNECT continue the approach manually or execute missed approach LOSS OF NAVIGATION INFORMATION Yellow flashing Mode annunciator ...

Page 156: ... to the OFF position pulling the AVIONICS MASTER circuit breaker will restore power to the avi onics buses TRANSPONDER FAILURE XPDR FAIL The display is not receiving information from the transponder 1 Confirm status of transponder with ATC If Transponder is inoperative 2 Traffic Advisory System TAS if installed STBY ENGINE AND OR FUEL DISPLAY FAILURE Indications which are not compatible with other...

Page 157: ...rom cruise tables in Section 5 PERFOR MANCE e EGT 4 Available Instruments MONITOR ERRONEOUS FAILURE DISPLAYS Erroneous Warning Caution or Advisory Alerts Red X s or Erroneous Exceedence displays There is a remote chance that an alert red X or red exceedence display may be erroneously displayed If it is suspected that an erroneous failure display has occurred 1 Use other system information to deter...

Page 158: ... chance that a system failure could occur WITHOUT an associated failure indication Alert Red X or Exceedence Display 1 Use other system information to determine if the system failure is valid If it cannot be determined that the system failure is the result of an erroneous display 2 Assume the failure is valid and follow the appropriate Emergency or Abnormal procedures FAILURE OF COOLING FANS PFD F...

Page 159: ... AUTONOMOUS INTEGRITY MONITORING RAIM During enroute oceanic terminal or initial approach phase of flight 1 Continue to navigate using GPS 2 Verify position using NAV 1 or NAV 2 every 15 minutes Or 3 Utilize NAV 1 or NAV 2 receivers During Final Approach 1 GPS navigation will continue for up to 5 minutes 2 Conduct missed approach 3 If terminal GPS sensitivity is lost during the missed approach rev...

Page 160: ...n or Obstacle Impact ITI or IOI Caution Voice caution alerts and annunciators are provided if the air plane flight path is projected to impact the terrain or an obsta cle within approximately 60 seconds In all cases a yellow TERRAIN will be displayed on the PFD and the MFD TAWS page if selected One of the following voice caution alerts will be heard REASON VOICE CAUTION ALERT Violation of Required...

Page 161: ...nts and visual observations in order to cancel the alert The voice caution alert will be repeated until the threat no longer exists 2 Advise Air Traffic Control as necessary EXCESSIVE DESCENT RATE CAUTION TERRAIN Voice Caution Alert Sink Rate Excessive Descent Rate EDR Caution A Voice caution alert and annunciator are provided if the airplane is below 5 000 feet and approaching the terrain at an e...

Page 162: ...vided to alert the pilot that the airplane is losing altitude after takeoff The cau tions will be provided whether or not the TAWS system is enabled The alerts are only active if all of the following condi tions are met The takeoff phase of flight The system must have detected an actual takeoff Alerts are not provided for go arounds or missed approaches The height above the terrain is less than 70...

Page 163: ...the glide path to cancel the alerts DITCHING OFF AIRPORT LANDING OR FLYING VFR AROUND UNIQUE TERRAIN Inhibit the visual and voice alerts of the TAWS system using the following procedure The terrain page will remain opera tional on the MFD and the GPWS functions will still be opera tional On the MFD 1 Large FMS Knob SELECT THE MAP GROUP 2 Small FMS Knob SELECT THE TAWS PAGE 3 Press the MENU Key 4 S...

Page 164: ... displays message in alerts window NOTE On some software versions exceeding a specific engine or electrical tolerance will cause the engine display to automatically revert to the default ENGINE page display Hence the following caution annunciations are not required Other software versions require the pilot to manually select the ENGINE page display and necessitate additional caution annunciations ...

Page 165: ...Power REDUCE AS REQUIRED 3 Mixture LEAN AS REQUIRED 4 Crossfeed if fuel imbalance 15 gals AS REQUIRED 5 Fuel Quantity MONITOR Do not take off if the fuel quantity display indicates in the yellow band or with less than 13 gallons in each wing fuel system ALTERNATOR LOAD HIGH ALT LOAD 1 Alternator load affected side CONFIRM 100 AMPS 2 Non essential electrical equipment OFF If load does not decrease ...

Page 166: ...epared to use standby instruments 5 Land at the nearest suitable airport SURFACE DEICE AIR PUMP L AIR PUMP or R AIR PUMP 1 Surface Deice Boots CHECK OPERATION 2 Deice pressure gage a While boots are inflating 9 to 20 PSI b When boots are fully inflated 15 PSI MINIMUM If boots operate normally 3 Operations in icing conditions at pilot s discretion avoid if possible Otherwise 4 Do not enter or conti...

Page 167: ...ting Battery 4 13 Cold Starts 4 13 Flooded Engine 4 14 Hot Starts 4 14 Before Taxi 4 15 Before Takeoff Runup 4 18 Before Takeoff Final Items 4 20 Takeoff 4 20 Climb 4 20 Cruise 4 22 Descent 4 22 Before Landing 4 23 Normal Landing 4 23 Balked Landing 4 23 After Landing 4 24 Shutdown and Securing 4 24 Other Normal Procedures 4 25 External Power 4 25 Engine Starting using External Power 4 25 ...

Page 168: ...trical 4 30 Monitoring the CHTs and EGTs 4 31 Avionics 4 31 Autopilot Flight Director 4 31 General 4 31 Autopilot Flight Director Procedures 4 32 Approach Procedures 4 41 Traffic Information Service TIS 4 45 L 3 Communications SKYWATCH SKY497 Traffic Advisory System if installed 4 45 Cold Weather Operation 4 46 Preflight Inspection 4 46 After Starting 4 47 Taxiing 4 47 Before Takeoff 4 48 Takeoff ...

Page 169: ...uel Vent Heat Stall Warning Heat Pitot Heat Windshield Heat and Ice Light 4 52 In Flight 4 52 Surface Deice System 4 53 Electrothermal Propeller Deice 4 53 Electrothermal Heated Windshield Segment 4 54 Pitot Heat Stall Warning Heat and Fuel Vent Heat 4 54 After Landing 4 54 Simulating One Engine Inoperative Zero Thrust 4 54 Practice Demonstration of VMCA 4 55 Engine Break In Information 4 56 Noise...

Page 170: ...Model G58 4 4 June 2011 Section 4 Normal Procedures THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 171: ...Climb VX 92 kts Two Engine Best Rate of Climb VY 105 kts Cruise Climb 136 kts Turbulent Air Penetration 156 kts Landing Approach 5400 lbs Flaps Down 30 95 kts Balked Landing Climb 95 kts Intentional One Engine Inoperative Speed VSSE 88 kts Air Minimum Control Speed VMCA 84 kts Minimum During Icing Conditions 130 kts NOTE Refer to all applicable Hawker Beechcraft Corpo ration Supplements and STC Su...

Page 172: ...del G58 Section 4 4 6 PREFLIGHT INSPECTION 1 CABIN a Emergency Exits CHECK 1 Safety Wire Beneath Cover INTACT 2 Windows CLOSED LOCKED b Seats and Seat Belts PROPERLY INSTALLED c Baggage SECURE TH04C 054024AA AI April 2008 ...

Page 173: ...IFY REVERSIONARY MODE 3 Soft Keys SELECT ENGINE SYSTEM 4 L Bus R Bus Voltages CHECK a L Bus 23 Volts minimum b R Bus 23 Volts minimum i Landing Gear Position Lights CHECK 3 GREEN j Annunciator Test Button PRESS Gear In Transit Light and Flap Lights ILLUMINATED k Exterior Interior Lights CHECK AS REQUIRED l Standby Attitude Indicator FLAG PULLED m L BAT R BAT OFF n Standby Attitude Indicator YELLOW...

Page 174: ... Beacon CHECK g Tie Down REMOVE 5 LEFT FUSELAGE a Cabin Air Intake CLEAR b Cabin Air Exhaust CLEAR c Static Port CLEAR d All Antennas CHECK e Lower Flashing Beacon CHECK 6 LEFT WING TRAILING EDGE a Fuel Sump Aft of Wheel Well DRAIN CHECK FUEL b Fuel Vents CLEAR c Flap CHECK d Aileron Trim Tab CHECK SECURITY ALIGNMENT WITH AILERON e Aileron CHECK MOVEMENT SECURITY f Static Wicks CHECK g Wing Tip CH...

Page 175: ...n REMOVE h ADC OAT Probe CHECK i Fuel Sight Gage CHECK j Engine Oil 10 QTS MINIMUM k Engine Cowling SECURE l Landing Light CHECK m Engine Air Intake CLEAR n Propeller Spinner CHECK Nicks Leaks Deice Boots o Cowl Flap CHECK p Left Main Gear CHECK 1 Gear Doors SECURE FLUSH 2 Landing Gear Uplock Roller CHECK 3 W O W Switch Linkage SECURE 4 Scissor Linkage SECURE 5 Shock Strut PROPER INFLATION 6 Tire ...

Page 176: ...artment CHECK 1 Brake Fluid Reservoir CHECK 2 Circuit Breakers CHECK 3 Baggage SECURE 4 Baggage Compartment Door CLOSE SECURE g Cabin Heater Over Temperature Switch CHECK h Heater Exhaust Outlet CHECK i Heater Fuel Drain Line CHECK 9 RIGHT WING LEADING EDGE a Fuel Strainer and Fuel Selector Drains DRAIN CHECK FUEL b Fuel Sump Drains DRAIN CHECK FUEL c Left Main Gear CHECK 1 Gear Doors SECURE FLUSH...

Page 177: ...eice Boots CHECK l Tie Down REMOVE m Fuel CHECK QTY O RING CAP SECURE Always check wing tip tank if installed first do not remove inboard cap if fuel is visible in tip tank n Wing Tip Tank Sump if installed DRAIN CHECK FUEL o Siphon Break Port CLEAR p Navigation and Strobe Lights CHECK 10 RIGHT WING TRAILING EDGE a Wing Tip CHECK b Static Wicks CHECK c Aileron CHECK MOVEMENT SECURITY d Flaps CHECK...

Page 178: ...ng Gear Handle DN 9 Throttles CLOSE 10 Propellers HIGH RPM 11 Mixture FULL RICH 12 Flaps UP 13 Cowl Flaps OPEN 14 Avionics Circuit Breakers IN 15 ELT Switch ARM 16 Battery System Check CONFIRM COMPLETE 17 L R BAT L R ALT ON 18 PFD VERIFY REVERSIONARY MODE 19 White TAWS TEST if installed ILLUMINATED Indicates TAWS B system test is in progress 20 Alerts CHECK CONSIDERED 21 White TAWS TEST if install...

Page 179: ...each tank 24 R Fuel Boost Pump VERIFY OPERATION a R Fuel Boost Pump SELECT LO LISTEN FOR OPERATION b R Fuel Boost Pump SELECT OFF 25 L Fuel Boost Pump VERIFY OPERATION a L Fuel Boost Pump SELECT LO LISTEN FOR OPERATION b L Fuel Boost Pump SELECT OFF ENGINE STARTING BATTERY Do not engage starter for more than 30 seconds in any 4 minute period COLD STARTS 1 Throttle FULL OPEN 2 Propeller HIGH RPM 3 ...

Page 180: ...ttle after start 900 to 1000 RPM 8 Oil Pressure CHECK Engine oil pressure must be out of the red band within 30 seconds 9 Other Engine START REPEAT STEPS 1 8 FLOODED ENGINE 1 Mixture CUT OFF 2 Propeller HIGH RPM 3 Throttle OPEN 4 Magneto Start Switch START Release to BOTH when engine starts 5 As Engine Starts a Throttle IDLE b Mixture FULL RICH HOT STARTS 1 Mixture CUT OFF 2 Propeller HIGH RPM 3 F...

Page 181: ... TAXI 1 Throttles 900 to 1000 RPM 2 Oil Pressure and Temperature CHECK Engine oil and oil pressure must be in green band prior to engine run up above 1200 RPM 3 Avionics Master ON 4 Autopilot Preflight Test COMPLETE a Red AFCS Message ILLUMINATED WHILE AHRS ALIGNS b Red AFCS Message EXTINGUISHED c White PFT Message ILLUMINATED 5 Seconds d White PFT Message EXTINGUISHED e Autopilot Disconnect Tone ...

Page 182: ...ONITOR INCREASE 2 Alerts BUSES TIED ILLUMINATED 3 L Bus and R Bus Voltage 27 5 29 0 Volts f L ALT ON 1 L Alt and R Alt Load POSITIVE 2 Alerts L ALT INOP BUSES TIED EXTINGUISHED 3 L Bus and R Bus Voltage 27 5 29 0 Volts g Steps d f REPEAT for R ALT 9 Lights AS REQUIRED 10 Avionics CHECK SET a Radios Comm and Nav b Altimeter c CDI Nav Source d Transponder e Altitude Preselect f Flight Plan 11 TAS if...

Page 183: ...FMS Knob SELECT Test TAWS e Press ENT Key f Verify a white TAWS TEST is displayed on the PFD g Verify the TAWS page turns black a yellow TAWS TEST is displayed in the center of the page and a white TAWS TEST is displayed in the lower right corner h Verify TAWS SYSTEM TEST OK is heard at the end of the test 13 Standby Attitude Indicator CHECK a Standby Battery CHECK IF DESIRED see OTHER NORMAL PROC...

Page 184: ... RPM 6 Propellers EXERCISE to obtain 200 to 300 RPM drop 7 Throttles 1700 RPM 8 Magnetos CHECK a Variance between individual magnetos should not exceed 50 RPM b Maximum drop should not exceed 150 RPM 9 Throttles 1500 RPM 10 Propellers FEATHERING CHECK a Move the propeller controls past the detent b Do not allow an RPM drop of more than 300 RPM on either engine Failure to observe the RPM limits dur...

Page 185: ...r NEUTRAL b Elevator SET WITHIN GREEN BAND 13 Flaps CHECK OPERATION SET FOR TAKEOFF 14 Flight Controls CHECK FREEDOM OF MOVEMENT AND PROPER DIRECTION OF TRAVEL 15 Doors and Windows SECURE Cabin Door Lock Indicator CHECK CLOSED 16 Fuel Selectors ON feel for detent confirm visually 17 Fuel Boost Pump OFF if ambient temperature is 32 C or above use LOW pressure boost 18 Alerts Messages EXTINGUISHED O...

Page 186: ...FUEL FLOW MARKER 2 Brakes RELEASE 3 Instruments CHECK MAP RPM Fuel Flow Oil Temp Press 4 Rotation Speed ROTATE 5 Landing Gear when positive R C established RETRACT CLIMB 1 Power SET a Throttles FULL FORWARD b Propellers MCP Climb 2700 RPM Cruise Climb 2500 RPM c Prop Sync ON d Mixtures MAINTAIN FUEL FLOW AT CYAN CLIMB FUEL FLOW MARKER NOTE The fuel flow marker will not revert to the Cruise Climb s...

Page 187: ...O and leaning the fuel flow to the cyan climb fuel flow marker The cyan climb fuel flow marker on the fuel flow indicator is programmed to follow the schedule noted below when climbing at 2700 RPM When climbing at 2500 RPM the fuel flow marker is programmed to follow a schedule which is 2 GPH less than that shown below PRESSURE ALTITUDE FT CYAN CLIMB FUEL FLOW MARKER 2700 RPM GPH SL 26 6 2000 25 9...

Page 188: ...using the ENGINE SYSTEM page or the LEAN PAGES the MFD should be kept at all time on the main ENGINE page DESCENT 1 Altimeter PFD and Standby SET 2 Cowl Flaps CONFIRM CLOSED 3 Power AS REQUIRED Avoid prolonged idle settings Cylinder head temperatures should not fall below the green band 4 Mixtures ENRICH AS REQUIRED The mixtures must be manually enriched as the airplane descends An optional proced...

Page 189: ...eel for detent confirm visually 4 Fuel Boost Pumps OFF OR LOW AS PER AMBIENT TEMPERATURE 5 Cowl Flaps AS REQUIRED 6 Mixture Controls FULL RICH or as required by field elevation 7 Landing Gear 152 kts or below DOWN AND CHECK 8 Landing Lights AS REQUIRED 9 Propellers HIGH RPM NORMAL LANDING 1 Flaps 122 kts or below FULL DOWN 2 Airspeed ESTABLISH NORMAL APPROACH SPEED 3 Yaw Damp OFF BALKED LANDING 1 ...

Page 190: ...rical Equipment OFF 4 Throttles 1000 RPM 5 Fuel Boost Pumps OFF 6 Mixture Controls CUT OFF 7 Magnetos OFF after engines stop 8 L ALT and R ALT OFF 9 L BAT and R BAT OFF 10 Standby Attitude Indicator if desired CHECK EMERGENCY MODE See OTHER NORMAL PROCEDURES 11 Control Locks INSTALL 12 Wheel Chocks INSTALL 13 Parking Brake RELEASE NOTE Induction air scoop covers included in the loose tools and acc...

Page 191: ...ive lead of the external power unit to the nega tive terminal of the external power receptacle 3 In order to prevent arcing ensure external power unit is off while the connection is being made ENGINE STARTING USING EXTERNAL POWER 1 L BAT and R BAT OFF 2 L ALT and R ALT OFF 3 Avionics Master Switch OFF 4 Electrical Equipment OFF 5 External Power Source SET OUTPUT THEN OFF 27 0 to 28 5 volts 6 Exter...

Page 192: ...y until the display stabilizes then released slowly The indicator may be damaged if knob is released with a snap BEFORE TAKEOFF Standby Battery Check The status of the standby battery may be checked as follows 1 STBY PWR Button PRESS AND HOLD UNTIL STBY PWR LED STARTS FLASHING places battery in one minute test mode 2 Green Test LED ILLUMINATED 3 Red Test LED EXTINGUISHED 4 Emergency LED Lighting I...

Page 193: ...ute Thus the red LED could illuminate towards the end of the test period and then extinguish when the test is complete without the pilot s knowledge unless the display is continually monitored SHUTDOWN During a normal shutdown the Standby Power LED will flash for approximately one minute after power is removed No action is required and the standby attitude indicator will auto matically shutdown af...

Page 194: ...on If the standby bat tery is allowed to completely drain it will have to be removed and serviced prior to the next flight The airplane power will not adequately recharge a completely drained battery Emergency Mode The emergency mode may be checked during shutdown after all power has been removed from the airplane as follows 1 L BAT and R BAT OFF 2 Amber Standby Power LED FLASHING 3 STBY PWR Butto...

Page 195: ...ressure power setting or less in the following manner See the following information in Section 5 PERFORMANCE MANIFOLD PRESSURE vs RPM graph for leaning limi tations CRUISE POWER SETTING tables The EIS Lean page is found on the MFD 1 ENGINE Softkey PRESS 2 LEAN Softkey PRESS a Rich of Peak Slowly lean the mixture and note the first cylinder EGT to peak Then enrich the mixture to the desired cruise ...

Page 196: ...en leaning to the rich side of peak switch the fuel boost pump to LO then lean as required 6 Changes in altitude and power settings require the peak EGT to be rechecked and the mixture reset 7 MFD Softkeys RETURN TO MAIN ENGINE PAGE NOTE A Lean Assist function is available through the Garmin software utilizing the CYL SLCT and ASSIST Softkeys Reference Garmin Cockpit Reference Guide for details on...

Page 197: ...OPILOT FLIGHT DIRECTOR GENERAL NOTE If above 150 KTS operation in the PIT mode can result in nuisance pitch pulsing when using the NOSE UP or NOSE DOWN command keys Transition to ALT FLC or VS mode prior to using NOSE UP or NOSE DOWN keys With the autopilot engaged recommended climb or descent rate is 800 fpm or less ...

Page 198: ......

Page 199: ...HT DIRECTOR GENERAL It is the responsibility of the Pilot to monitor the autopilot when it is engaged The pilot should be prepared to immediately discon nect the autopilot and take prompt correc tive action in the event of unexpected or unusual autopilot behavior Do not attempt to manually fly the airplane with the autopilot engaged except when using the Control Wheel Steering CWS button The autop...

Page 200: ...to re engaging the autopilot AUTOPILOT FLIGHT DIRECTOR PROCEDURES The following are basic guidelines for operation of the autopilot and Flight Director They are one way but not necessarily the only way of operating the AFCS See Section 2 LIMITA TIONS Section 3 EMERGENCY PROCEDURES Section 3A ABNORMAL PROCEDURES Section 7 SYSTEMS DESCRIPTION and the Garmin G1000 Cockpit Reference Guide or G1000 Pil...

Page 201: ... Key if required PRESS VOR or GPS or LOC Displayed Disengaging the Autopilot or Autopilot Yaw Damper When the autopilot is manually disengaged the green AP will change to a black AP on a yellow background flash for 5 sec onds then extinguish and a 2 second aural alert will sound The YD will also change color and flash if it disconnects To disengage only the AP and leave the FD and YD engaged use o...

Page 202: ...g Knob SET DESIRED HEADING a Press knob to select existing heading b Rotate knob to select a new heading c New heading will be displayed in box to left of HSI for 3 seconds 2 HDG Key PRESS HDG Displayed 3 The airplane will turn in the direction the HDG bug is moved unless the heading change is greater than 340 Use of Navigation Mode GPS VOR LOC or BC If not initially established on the desired cou...

Page 203: ...will change from cyan digits on a black background to black digits on a cyan background and the box will flash for 5 seconds b At 300 feet from the desired altitude a cyan altitude reference bug will be visible on the left side of the alti tude display opposite the desired altitude c At 200 feet from the desired altitude the altitude in reference box returns to cyan digits on a black back ground w...

Page 204: ...s displayed in window above the altimeter display 2 Deselect other vertical modes VS or FLC if required 3 Green PIT and White ALT DISPLAYED IN AFCS STATUS BAR 4 NOSE UP or NOSE DN Key PRESS AS REQ TO SET CLIMB OR DESCENT PITCH ATTITUDE each press changes pitch by 0 5 degrees or 5 CWS Switch PRESS AND HOLD WHILE ADJUSTING PITCH THEN RELEASE Pitch reference will change to that which exists when swit...

Page 205: ...de VNV if installed NOTE Vertical navigation will only function when the navigation source is GPS The airplane s head ing must be within 75 degrees of the desired GPS course and within 10 NM cross track error in order for VNAV to function VNAV functions only for enroute and terminal descents Vertical navigation is not available dur ing climbs or descents between the final approach fix FAF and the ...

Page 206: ...he flashing VPTH and the autopi lot will capture and track the vertical profile If the VNV softkey is not pressed or the altitude preselect is not reset to a lower alti tude VPTH stops flashing at the TOD and the airplane will remain in ALT mode and not descend 4 At TOD VERIFY a Green VPTH in the AFCS status window on PFD b White ALTS or ALTV in the AFCS armed window on PFD c Airplane tracks verti...

Page 207: ...RESS a Green VS and green current vertical speed XXXXFPM displayed in AFCS status bar b Current vertical speed displayed in window above for a climb or below for a descent the Vertical Speed display c Cyan VS Reference bug displayed on left side of VS display d White ALT Displayed in AFCS Status Bar 3 NOSE UP or NOSE DN Key PRESS AS REQ TO SET CLIMB OR DESCENT VS each press changes VS by 100 fpm o...

Page 208: ...eady Use of the Flight Level Change Mode FLC 1 ALT Knob SET DESIRED LEVEL OFF ALTITUDE a Preset Altitude is displayed in window above the altimeter display NOTE If the Flight Director is in Altitude Hold green ALT XXXXXFT displayed in the AFCS status bar the desired altitude must be set either above or below the Altitude Hold value for the FLC mode to function 2 FLC Key PRESS a Green FLC and green...

Page 209: ...ence airspeeds are 210 and 90 Kts 7 Upon Reaching the Preset Altitude the green FLC XXXKT and white ALT will be replaced by a green ALT and XXXXXFT and the green ALT will flash for 10 seconds and then become steady APPROACH PROCEDURES VOR or ILS Approaches VAPP or LOC GS 1 CDI Key SELECT VOR 1 OR VOR 2 2 CRS Knob SET REQUIRED COURSE 3 HDG Knob SELECT INTERCEPT HEADING 4 HDG Key PRESS HDG Displayed...

Page 210: ...R Key PRESS GPS Displayed 4 Airspeed ESTABLISH 5 PFD VERIFY GPS APR MODE WITHIN 2 NM OF FAF GPS Approach LPV or L VNAV Software Version 0857 05 or 0857 06 1 Baro Minimums SET 2 CDI Key SELECTED GPS 3 Approach VERIFY ACTIVATED 4 APR Key PRESS Green GPS and White GP Displayed 5 Airspeed ESTABLISH 6 AFSC Status Bar VERIFY GPS AND GP MODES ARE CAPTURED June 2011 ...

Page 211: ...S ARE CAPTURED NOTE During LNAV V approaches it will be nec essary to follow the glide path using either the VS or PITCH modes in order for the airplane to level off at the preselected MDA Back Course Approach BC 1 CDI Key SELECT VOR 1 OR VOR 2 2 CRS Knob SET TO ILS FRONT COURSE 3 HDG Knob SELECT INTERCEPT HEADING 4 HDG Key PRESS HDG Displayed 5 NAV Key PRESS White BC Displayed 6 Airspeed ESTABLIS...

Page 212: ...S MISSED APPROACH SEQUENCE 8 ALT Knob if required SET ALTITUDE At 400 feet minimum 9 AP Key PRESS TO ENGAGE AUTOPILOT 10 CWS PRESS TO CNX GA MODE ADJUST PITCH 11 HDG or NAV Key PRESS Go Around GA GA With an Active Approach Loaded Software Version 0857 05 or 0857 06 1 Go Around Button on Throttle PRESS 2 Throttles and Propellers FULL FORWARD 3 Flaps UP 4 Landing Gear UP 5 Missed Approach EXECUTE 6 ...

Page 213: ...ap page of the Map Group 4 Rotate the RANGE knob to change the display range L 3 COMMUNICATIONS SKYWATCH SKY497 TRAFFIC ADVISORY SYSTEM TAS IF INSTALLED The SKY497 can only detect aircraft that are equipped with operating transponders 1 Traffic information shown on the PFD and MFD is pro vided as an aid in visually acquiring traffic Pilots must maneuver the airplane based only upon ATC guidance or...

Page 214: ...gee or mop may be used to clear snow that is not adhering to the surfaces Airfoil contours may be altered by the ice and snow to the extent that their lift qualities will be seriously impaired Ice and snow on the fuselage can increase drag and weight Frost that may accumulate on the wing the tail sur faces or on any control surface must be removed prior to flight Conditions for accumulating moistu...

Page 215: ...AFTER STARTING If there is no oil pressure within the first 30 seconds after start or if oil pressure drops after a few minutes of ground operation shut down and check for broken oil lines oil cooler leaks or congealed oil NOTE It is advisable to use external power for starting in cold weather During warm up monitor engine temperature closely since it is quite possible to exceed the cylinder head ...

Page 216: ...s on the runway Extra cycling of the landing gear when above 500 feet AGL may help clear any contamination from the gear system DESCENT During descent and landing give special attention to engine temperatures since the engines will have a tendency toward overcooling LANDING Braking and steering are less effective on slick runways Also hydroplaning may occur under wet runway conditions at higher sp...

Page 217: ...ay 2 Heater Switch ON 3 Heater Blower Switch ON NOTE Blower will automatically turn off when the landing gear is retracted 4 Cabin Heat Control PULL AFT TO INCREASE TEMPERATURE 5 Pilot Air Copilot Air Defrost Controls PULL OUT TO INCREASE AIR FLOW To Increase Heat To The Cabin 6 Pilot Air Copilot Air Defrost Controls PUSH IN To Turn Heater Off During Ground Operations 7 Cabin Heat Control PUSH IN ...

Page 218: ...hrough Windshield Is Insufficient For Landing 6 Pilot s Storm Window OPEN ICE PROTECTION SYSTEMS Airplanes are approved for flight in icing conditions only when properly equipped and operated per the procedures herein and the applicable Title 14 CFRs No multiengine airplane is approved for flight into severe icing conditions and none are intended for indefinite flight in continuous icing condition...

Page 219: ...inimum deice pressure b Check visually for hold down when cycle is complete 3 Right Throttle IDLE 4 Left Throttle 2000 RPM Repeat Step 2 5 Surface Deice MAN down UNTIL PRESSURE PEAKS not more than 8 seconds Then RELEASE a Check visually for inflation and 15 psi minimum deice pressure b Check visually for hold down when cycle is complete 6 Left Throttle IDLE ELECTROTHERMAL PROPELLER DEICE 1 Propell...

Page 220: ...KIAS This applies to all phases of flight except takeoff and landing If air speed is decreasing due to ice accumula tion and power or altitude changes fail to curtail airspeed deceleration alter flight to exit icing conditions before speeds of less than 130 KIAS are reached Flight in icing conditions may eventually cause the cowling inlets to become partially blocked resulting in higher cylinder h...

Page 221: ...Boots Are Fully Inflated 15 PSI MINIMUM 3 Repeat AS REQUIRED Rapid cycles in succession or cycling before at least 1 2 inch of ice has accumu lated may cause the ice to grow outside the contour of the inflated boots and prevent ice removal NOTE Either engine will supply sufficient vacuum and pressure for deice operation ELECTROTHERMAL PROPELLER DEICE Propeller Deice ON the system may be operated c...

Page 222: ...E ENGINE INOPERATIVE ZERO THRUST Use the following power setting only on one engine at a time to establish zero thrust Use of this power setting avoids the difficulties of restarting an engine and preserves the availability of power to counter potential hazards The following procedure should be accomplished by alternat ing small reductions of propeller and then throttle until the desired setting h...

Page 223: ...simulated inoperative engine IDLE 6 Throttle other engine MAXIMUM MANIFOLD PRESSURE 7 Airspeed REDUCE APPROXIMATELY 1 KNOT PER SECOND UNTIL EITHER VMCA OR STALL WARNING IS OBTAINED Use rudder to maintain directional control heading and ailerons to maintain 5 bank towards the operative engine lateral atti tude At the first sign of either VMCA or stall warning which may be evidenced by inability to ...

Page 224: ...the surface weather permitting even though flight at a lower level may be consistent with the provisions of govern ment regulations NOTE The preceding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instruc tions or where in the pilot s judgement an altitude of less than 2 000 feet is necessary to adequately exercise his duty to see and avoid ot...

Page 225: ...d and Fuel Requirement 5 11 Cruise Climb 5 11 Cruise 5 12 Descent 5 14 Time Fuel Distance Summary 5 14 Reserve Fuel 5 14 Total Fuel Required 5 15 Landing 5 15 Balked Landing Climb Performance 5 15 Graphs Airspeed Calibration Normal System 5 17 Altimeter Correction Normal System 5 18 Airspeed Calibration Emergency System 5 19 Altimeter Correction Emergency System 5 20 ISA Conversion 5 21 Fahrenheit...

Page 226: ... Ceiling One Engine Inoperative 5 33 Time Fuel and Distance to Cruise Climb 5 34 Tables Maximum Cruise Power 25 in Hg 2500 RPM Rich 5 36 Recommended Cruise Power 25 in Hg 2500 RPM Lean 5 37 23 in Hg 2300 RPM Rich 5 38 23 in Hg 2300 RPM Lean 5 39 Graphs Cruise Speeds Rich 5 40 Cruise Speeds Lean 5 41 Range Profile 166 Gallons Rich 5 42 Range Profile 166 Gallons Lean 5 43 Endurance Profile 166 Gallo...

Page 227: ... Performance TABLE OF CONTENTS CONT D SUBJECT PAGE Endurance Profile 194 Gallons Rich 5 48 Endurance Profile 194 Gallons Lean 5 49 Holding Time 5 50 Time Fuel and Distance to Descend 5 51 Climb Balked Landing 5 52 Landing Distance 5 53 ...

Page 228: ...Model G58 5 4 July 2014 Section 5 THIS PAGE INTENTIONALLY LEFT BLANK Performance ...

Page 229: ...face deice boots are inflated 2 Residual ice on the airplane can disrupt the airflow over lifting surfaces and may cause an increase in the stall speeds and a change in the amount of warning provided by the stall warning vane 3 The wings stabilizers and all control surfaces must be cleared of frost ice or snow prior to takeoff 4 Ice accumulations on unprotected surfaces will decrease climb rates c...

Page 230: ...the same PROPORTIONAL DISTANCE between the guideline above and guideline below the projected line For instance if the projected line intersects the reference line in the ratio of 30 down 70 up between the guide lines then maintain this same 30 70 relationship between the guidelines all the way to the next known item or answer 3 The associated conditions define the specific conditions from which pe...

Page 231: ...in Hg Runway 26L Length 10 004 ft Wind 300 at 13 kts At Destination Outside Air Temperature 25 C 77 F Field Elevation 3605 ft Altimeter Setting 29 56 in Hg Wind 190 at 12 kts Runway 22 Length 13 502 ft ROUTE SEGMENT AVERAGE MAGNETIC COURSE AVERAGE MAGNETIC VARIATION DIST NM WIND AT 11 500 FEET DIR KTS OAT 11 500 FEET C LEG A 155 12 E 51 010 30 5 LEG B 153 12 E 40 010 30 5 LEG C 135 12 E 74 100 20 ...

Page 232: ...e Pressure Altitude at the departure airport is 320 ft above the field elevation 5333 320 5653 ft Pressure Altitude at Destination 29 92 29 56 0 36 in Hg 0 36 x 1000 360 ft The Pressure Altitude at the destination airport is 360 ft above the field elevation 3605 360 3965 ft NOTE For flight planning the difference between cruise altitude and cruise pressure altitude has been ignored TAKE OFF WEIGHT...

Page 233: ...nd 10 knots headwind component Accelerate Stop Distance 3960 ft NOTE Since 3960 ft is less than the available field length of 10 004 ft the accelerate stop pro cedure can be performed at any weight Take off at 5500 lbs can be accomplished However if an engine failure occurs before becoming airborne the acceler ate stop procedure must be performed The following example assumes the airplane is loade...

Page 234: ...00 lbs Climb Gradient 2 6 A 2 6 climb gradient is 26 ft of vertical height per 1000 ft of horizontal distance NOTE The Take off Climb Gradient One Engine Inoperative graph assumes zero wind con ditions Climbing into a headwind will result in higher angles of climb and hence better obstacle clearance capabilities Calculation of horizontal distance to clear an obstacle 90 ft above the runway surface...

Page 235: ...sure altitude Then trace right to 5500 lbs and then down to obtain the time fuel and distance to climb from S L to 5653 ft Repeat the process starting with the cruise tempera ture of 5 C cruise altitude of 11 500 ft and initial cruise weight of 5500 lbs to obtain the time fuel and distance to climb from S L to 11 500 ft Subtract the former values from the latter values to obtain the time fuel and ...

Page 236: ...the OAT Box located in the lower left corner of the PFD For temperature values between ISA and ISA 20 C interpolate to determine the cruise power setting Enter the ISA CONVERSION Graph at 11 500 ft and the true temperature for the route segment Enter the MAXIMUM CRUISE POWER table at 10 000 ft and at 12 000 ft at ISA and ISA 20 C ROUTE SEGMENT OAT ISA CONDITION LEG A B 5 C ISA 3 C LEG C 0 C ISA 8 ...

Page 237: ...ce required to climb or descend has been subtracted from segment distance ROUTE SEGMENT ISA CONDITION FUEL FLOW PER ENG GAL HR TAS KNOTS LEG A B ISA 3 C 14 0 196 LEG C ISA 8 C 13 9 196 LEG D ISA 17 C 13 6 197 LEG E ISA 18 C 13 6 197 ROUTE SEGMENT DISTANCE NM EST GROUND SPEED KNOTS TIME AT CRUISE ALTITUDE HRS MIN FUEL USED CRUISE GAL LEG A 30 5 224 08 2 3 8 LEG B 40 0 223 10 8 5 0 LEG C 74 0 182 24...

Page 238: ...r values to obtain the time fuel and distance to descend from 11 500 ft to 3695 ft Time to Descend 23 7 8 15 2 min Fuel Used to Descend 8 7 2 8 5 9 gal Descent Distance 70 22 48 NM TIME FUEL DISTANCE SUMMARY Total Flight Time 1 hour 42 2 min Block Speed 322 NM 1 hour 42 2 min 189 kts RESERVE FUEL Enter the ECONOMY CRUISE POWER table at ISA and ISA 20 C at 10 000 ft and 12 000 ft Interpolate to fin...

Page 239: ...amp Weight 5524 lbs Estimated Fuel 52 0 gal at 6 lbs gal 312 lbs Estimated Landing Weight 5524 312 5212 lbs NOTE For the Landing Distance example a 5039 lbs weight and a 9 5 kts headwind compo nent were assumed Enter the LANDING DISTANCE graph at 25 C 3965 ft pres sure altitude 5039 lbs landing weight an 9 5 kts headwind component Ground Roll 1450 ft Total Distance over 50 ft Obstacle 2500 ft Appr...

Page 240: ...Performance Model G58 Section 5 5 16 Enter the CLIMB BALKED LANDING graph at 25 C 3965 ft pressure altitude and 5166 lbs Rate of Climb 765 ft min Climb Gradient 6 9 July 2014 ...

Page 241: ...Performance Section 5 Model G58 5 17 July 2014 58 590000 67A11_sec05fo fm Page 1 Tuesday July 29 2014 8 36 AM ...

Page 242: ...Performance Model G58 Section 5 5 18 July 2014 58 590000 67A11_sec05fo fm Page 2 Tuesday July 29 2014 8 36 AM ...

Page 243: ...Performance Section 5 Model G58 5 19 July 2014 58 590000 67A11_sec05fo fm Page 3 Tuesday July 29 2014 8 36 AM ...

Page 244: ...Performance Model G58 Section 5 5 20 July 2014 58 590000 67A11_sec05fo fm Page 4 Tuesday July 29 2014 8 36 AM ...

Page 245: ...Performance Section 5 Model G58 5 21 July 2014 58 590000 67A11_sec05fo fm Page 5 Tuesday July 29 2014 8 36 AM ...

Page 246: ...Performance Model G58 Section 5 5 22 July 2014 58 590000 67A11_sec05fo fm Page 6 Tuesday July 29 2014 8 36 AM ...

Page 247: ...Performance Section 5 Model G58 5 23 July 2014 ...

Page 248: ...Performance Model G58 Section 5 5 24 July 2014 58 590000 67A11_sec05fo fm Page 7 Tuesday July 29 2014 8 36 AM ...

Page 249: ...Performance Section 5 Model G58 5 25 July 2014 ...

Page 250: ...Performance Model G58 Section 5 5 26 July 2014 ...

Page 251: ...Performance Section 5 Model G58 5 27 July 2014 58 590000 67A11_sec05fo fm Page 8 Tuesday July 29 2014 8 36 AM ...

Page 252: ...Performance Model G58 Section 5 5 28 July 2014 58 590000 67A11_sec05fo fm Page 9 Tuesday July 29 2014 8 36 AM ...

Page 253: ...Performance Section 5 Model G58 5 29 July 2014 58 590000 67A11_sec05fo fm Page 10 Tuesday July 29 2014 8 36 AM ...

Page 254: ...Performance Model G58 Section 5 5 30 July 2014 58 590000 67A11_sec05fo fm Page 11 Tuesday July 29 2014 8 36 AM ...

Page 255: ...Performance Section 5 Model G58 5 31 July 2014 58 590000 67A11_sec05fo fm Page 12 Tuesday July 29 2014 8 36 AM ...

Page 256: ...Performance Model G58 Section 5 5 32 July 2014 58 590000 67A11_sec05fo fm Page 13 Tuesday July 29 2014 8 36 AM ...

Page 257: ...UM CONTINUOUS LANDING GEAR UP INOPERATIVE PROPELLER FEATHERED FLAPS UP MIXTURE AS REQUIRED BY ALTITUDE EXAMPLE OAT 20 C WEIGHT 4700 LBS SERVICE CEILIN 12 015 FT NOTE ONE ENGINE INOPERATIVE SERVICE CEILING IS THE MAXIMUM PRESSURE ALTITUDE AT WHICH THE AIRPLANE HAS THE CAPABILITY OF CLIMBING AT 50 FT MINUTE WITH ONE PROPELLER FEATHERED July 2014 ...

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Page 260: ... 109 105 98 92 86 80 74 98 101 105 102 95 89 83 77 72 95 98 101 98 92 86 80 75 70 25 25 25 24 22 21 19 18 16 25 25 25 24 22 21 19 18 16 25 25 25 24 22 21 19 18 16 23 16 9 2 6 13 20 27 34 59 52 45 38 30 23 16 9 2 95 88 81 74 66 59 52 45 38 5 9 13 17 21 25 29 33 37 15 11 7 3 1 5 9 13 17 35 31 27 23 19 15 11 7 3 PRESS ALT MAN PRESS OAT FUEL FLOW ENGINE AIR SPEED OF PEAK EGT FEET C F IN HG PPH GPH KIA...

Page 261: ...87 91 94 91 84 78 72 67 62 84 87 91 88 81 75 70 65 60 81 84 87 84 78 72 67 62 58 25 25 25 24 22 21 19 18 16 25 25 25 24 22 21 19 18 16 25 25 25 24 22 21 19 18 16 23 16 9 2 6 13 20 27 34 59 52 45 38 30 23 16 9 2 95 88 81 74 66 59 52 45 38 5 9 13 17 21 25 29 33 37 15 11 7 3 1 5 9 13 17 35 31 27 23 19 15 11 7 3 PRESS ALT MAN PRESS OAT FUEL FLOW ENGINE AIR SPEED OF PEAK EGT FEET C F IN HG PPH GPH KIAS...

Page 262: ...1 84 87 91 89 84 78 73 68 78 79 85 88 87 81 76 71 66 76 79 82 85 84 78 73 68 64 23 23 23 23 22 21 19 18 17 23 23 23 23 22 21 19 18 17 23 23 23 23 22 21 19 18 17 23 16 9 2 6 13 20 27 34 59 52 45 38 30 23 16 9 2 95 88 81 74 66 59 52 45 38 5 9 13 17 21 25 29 33 37 15 11 7 3 1 5 9 13 17 35 31 27 23 19 15 11 7 3 PRESS ALT MAN PRESS OAT FUEL FLOW ENGINE AIR SPEED OF PEAK EGT FEET C F IN HG PPH GPH KIAS ...

Page 263: ...8 67 70 73 76 75 69 64 60 56 64 67 70 73 72 67 62 58 54 62 65 68 70 69 64 60 56 52 23 23 23 23 22 21 19 18 17 23 23 23 23 22 21 19 18 17 23 23 23 23 22 21 19 18 17 23 16 9 2 6 13 20 27 34 59 52 45 38 30 23 16 9 2 95 88 81 74 66 59 52 45 38 5 9 13 17 21 25 29 33 37 15 11 7 3 1 5 9 13 17 35 31 27 23 19 15 11 7 3 PRESS ALT MAN PRESS OAT FUEL FLOW ENGINE AIR SPEED OF PEAK EGT FEET C F IN HG PPH GPH KI...

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Page 265: ...Performance Section 5 Model G58 5 41 July 2014 ...

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Page 273: ...Performance Section 5 Model G58 5 49 July 2014 58 590000 67A11_sec05fo fm Page 22 Tuesday July 29 2014 8 36 AM ...

Page 274: ...PPLICABLE FOR ALL TEMPERATURES ASSOCIATED CONDITIONS POWER SETTINGS 21 IN HG OR FULL THROTTLE AT 2100 RPM MIXTURE 20 C LEAN OF PEAK EGT WEIGHT 5200 LBS EXAMPLE FUEL AVAILABLE FOR HOLDING 50 GAL PRESSURE ALTITUDE 11 500 FT HOLDING TIME 2 6 HRS July 2014 ...

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Page 278: ...Performance Model G58 Section 5 5 54 THIS PAGE INTENTIONALLY LEFT BLANK July 2014 ...

Page 279: ... 6 Basic Empty Weight and Balance Form 6 9 Weight and Balance Record 6 10 Payload Locations 6 12 Weight and Balance Diagram 6 13 Moment Limits vs Weight Table 6 14 Loading Computing Procedure 6 15 Weight and Balance Loading Form 6 17 Useful Load Payload Weights and Moments Table 6 19 Occupants 6 19 Baggage 6 20 Useful Load Weight and Moments Table 6 21 Usable Fuel 6 21 Equipment List Prepared on a...

Page 280: ...Model G58 6 2 December 2009 Section 6 THIS PAGE INTENTIONALLY LEFT BLANK Wt and Bal Equip List ...

Page 281: ...Wt and Bal Equip List Section 6 Model G58 6 3 BASIC EMPTY WEIGHT AND BALANCE ACTUAL THIS PAGE TO BE REPLACED UPON AIRCRAFT DELIVERY December 2009 ...

Page 282: ...Wt and Bal Equip List Model G58 Section 6 6 4 SAMPLE LOADING THIS PAGE TO BE REPLACED UPON AIRCRAFT DELIVERY December 2009 ...

Page 283: ...lane Pilot in Command is responsible for the airplane to be properly loaded for each flight All pertinent weight and balance loading data is presented in this POH AFM Section The airplane weight and center of gravity limits are shown on the Weight and Balance Diagram page with the moment limits shown in the Moment Limits vs Weight Table A blank Weight and Balance Loading Form along with Computing ...

Page 284: ...ction 6 6 6 WEIGHING INSTRUCTIONS 357 36 C95TH06C2443 REAR JACK POINT FS 271 0 LEVELING POINTS FS 152 25 FRONT JACK POINTS FS 83 1 106 8 IN APPROX FS 40 0 LE MAC 67 2 IN MAC 63 1 IN REFERENCE DATUM FS 0 0 DIMENSIONAL DATA December 2009 ...

Page 285: ... remainder of the unusable fuel to be added to a drained system is 30 3 pounds at Fuse lage Station 78 5 3 Engine oil must be at the full level or completely drained Total engine oil when full is 45 pounds at Fuselage Sta tion 43 4 To determine airplane configuration at time of weighing installed equipment is checked against the airplane equipment list or superseding forms All installed equip ment...

Page 286: ...ctions will be approximately at Fuselage Station 96 7 for main wheels and Fuselage Station 10 3 for the nose wheel 7 Jack point weighings are accomplished by placing scales at the jack points specified in step 1 above Since the center of gravity of the airplane is forward of Fuse lage Station 83 1 the tail reaction of the airplane will be in an up direction This can be measured on regular scales b...

Page 287: ...2AA AI BASIC EMPTY WEIGHT NOTE Basic Empty Weight includes full engine oil and unusable fuel LEFT MAIN RIGHT MAIN G58 NOSE OR TAIL TOTAL AS WEIGHED ADD DRAINABLE UNUSABLE FUEL 30 3 78 5 2379 11 6 9 8 96 0 97 0 BARON 83 1 271 0 SER NO REG NO DATE December 2009 ...

Page 288: ...Wt and Bal Equip List Model G58 Section 6 6 10 December 2009 ...

Page 289: ...Wt and Bal Equip List Section 6 Model G58 6 11 December 2009 ...

Page 290: ...m Baggage Weight is 400 pounds aft of the Rear Spar with 5th and 6th seats removed or 200 pounds with only the 5th or 6th seat removed Notes 1 The floor structure load limit is 50 pounds per square foot between the front and rear spars and 100 pounds per square foot aft of the rear spar 2 Any combination of the 3rd 4th 5th and 6th seats may be removed by the Owner Operator or Pilot in Command with...

Page 291: ... 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000 5100 5200 5300 5400 5500 5600 5700 72 74 76 78 80 82 84 86 88 78 3 MAX LANDING WT MAX RAMP WT 5524 LB CENTER OF GRAVITY FUSELAGE STATION INCHES AFT OF DATUM WEIGHT POUNDS MAX TAKE OFF WT December 2009 ...

Page 292: ...850 4900 4950 5000 5050 5100 5150 5200 5250 5300 5350 5400 5450 5500 2812 2849 2886 2923 2960 2997 3034 3071 3108 3152 3196 3241 3285 3330 3375 3420 3465 3510 3556 3601 3647 3693 3740 3786 3832 3879 3926 3973 4020 4067 4115 4163 4210 4258 4307 3268 3311 3354 3397 3440 3483 3526 3569 3612 3655 3698 3741 3784 3827 3870 3913 3956 3999 4042 4085 4128 4171 4214 4257 4300 4343 4386 4429 4472 4515 4558 4...

Page 293: ...o the Useful Load Weights and Moments Tables 2 Record the weight arm optional and corresponding moment 100 from the appropriate Useful Load Pay load Weights and Moments Table for each payload item on lines 2 through 9 3 Total the weight column and moment 100 column to determine the Zero Fuel Weight on line 10 Calculate the arm 4 Record the weight and corresponding moment 100 for the total fuel loa...

Page 294: ...ble Fuel Table Interpolation may be necessary 9 Copy the Zero Fuel Weight from Line 10 to Line 18 and the fuel remaining from Line 17 to Line 19 Add the Line 19 weight and moment 100 to the Line 18 values to determine the Landing Weight on Line 20 Calculate the arm 10 Refer to the Moment Limits vs Weight Table or the Weight and Balance Diagram and ensure that the Zero Fuel Weight Take Off Weight a...

Page 295: ...r 150 0 8 Baggage Aft Compartment 180 0 9 Other 10 ZERO FUEL WEIGHT 11 Fuel Load 12 RAMP WEIGHT DO NOT EXCEED 5524 LB 13 Less Fuel for Start Taxi and Run Up 14 TAKE OFF WEIGHT DO NOT EXCEED 5500 LB 15 Fuel Load from Line 11 16 Less Fuel to Destination including Start Taxi and Run up from Line 13 17 Fuel Remaining Moment 100 from Usable Fuel Table 18 Zero Fuel Weight from Line 10 19 Add Fuel Remain...

Page 296: ...r 150 0 8 Baggage Aft Compartment 180 0 9 Other 10 ZERO FUEL WEIGHT 11 Fuel Load 12 RAMP WEIGHT DO NOT EXCEED 5524 LB 13 Less Fuel for Start Taxi and Run Up 14 TAKE OFF WEIGHT DO NOT EXCEED 5500 LB 15 Fuel Load from Line 11 16 Less Fuel to Destination including Start Taxi and Run up from Line 13 17 Fuel Remaining Moment 100 from Usable Fuel Table 18 Zero Fuel Weight from Line 10 19 Add Fuel Remain...

Page 297: ...128 135 143 150 82 90 98 107 115 123 131 139 148 156 164 111 122 133 144 155 167 178 189 200 211 222 115 127 138 150 161 173 184 196 207 219 230 115 127 138 150 161 173 184 196 207 219 230 120 132 144 156 168 180 192 204 216 228 240 152 167 182 198 213 228 243 258 274 289 304 Note Occupant Arms and Moments 100 for adjustable seats are shown at their extreme positions Intermediate positions 0 75 in...

Page 298: ...0 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 240 260 280 300 320 340 360 380 400 2 3 5 6 8 9 11 12 14 15 17 18 20 21 23 24 26 27 29 30 32 33 36 39 42 45 11 22 32 43 54 65 76 86 97 108 119 130 140 151 162 173 184 194 205 216 15 30 45 60 75 90 105 120 135 150 165 180 195 210 225 240 255 270 285 300 15 30 45 60 75 90 105 120 135 150 165 180 195 210 225 240 255 270 285 300 330 ...

Page 299: ...al Moment 100 lb in 10 60 46 46 20 120 92 92 30 180 140 140 40 240 189 189 50 300 238 238 60 360 288 288 70 420 338 338 80 480 388 388 90 540 439 439 100 600 489 489 110 660 539 539 120 720 590 590 130 780 641 641 140 840 692 692 150 900 743 743 160 960 793 793 166 996 824 824 170 1020 845 180 1080 899 190 1140 953 194 1164 974 December 2009 ...

Page 300: ...Wt and Bal Equip List Model G58 Section 6 6 22 THIS PAGE INTENTIONALLY LEFT BLANK December 2009 ...

Page 301: ...7 8 Flight Navigational Instrument Panel 7 8 Subpanel 7 9 OAT Gage TH 2125 thru TH 2339 except TH 2310 7 9 Pedestal 7 9 Illustrations 7 11 Typical Instrument Panel 7 11 Pilot s and Copilot s Subpanel 7 12 Pedestal 7 13 Left Circuit Breaker Panel 7 14 Ground Control 7 15 Wing Flaps 7 15 Landing Gear System 7 16 Control Switch 7 16 Position Lights 7 16 Safety Switches 7 17 Warning Horn and GEAR UP A...

Page 302: ...sses 7 23 Doors Windows and Exits 7 24 Cabin Door 7 24 Utility Doors 7 25 Operation With Aft Utility Doors Removed 7 25 Openable Cabin Windows 7 26 Control Locks 7 27 Engines 7 29 Engine Controls 7 29 Throttles Propellers and Mixtures 7 29 Induction Air 7 29 Engine Ice Protection 7 30 Engine Lubrication 7 30 Cowl Flaps 7 31 Propellers 7 31 Propeller Synchronizer 7 32 Propeller Sync Pointer 7 32 Fu...

Page 303: ... Pumps 7 38 Fuel Boost Pumps 7 38 LO Position 7 38 HI Position 7 39 Fuel Off Loading 7 39 Fuel Required For Flight 7 39 Electrical System 7 39 Power Sources 7 39 Protective Devices 7 40 Distribution 7 41 Electrical Schematic Diagram 7 43 Left Avionics Electrical Equipment Bus Connection 7 44 Right Avionics Electrical Equipment Bus Connection 7 46 Monitoring The Electrical System 7 48 Electrical Al...

Page 304: ... Pitot System 7 57 Pitot Heat 7 57 Normal Static Air System 7 57 Emergency Static Air System 7 57 Pitot and Static System Schematic 7 58 Stall Warning 7 59 Ice Protection Systems 7 59 Surface Deice System 7 59 Electrothermal Heated Windshield Segment 7 60 Electrothermal Propeller Deice 7 61 Pitot Heat 7 61 Stall Warning Anti Ice 7 61 Heated Fuel Vents 7 62 Engine Break In Information 7 62 Avionics...

Page 305: ...eather Radar GWX 7 69 Engine Indicating System 7 69 Engine Display 7 70 Alerting System 7 71 Airplane Alerts and Messages 7 73 Autopilot 7 75 GFC 700 Automatic Flight Control System AFCS 7 75 Components 7 75 PFD Displays 7 76 Autopilot Disconnects 7 78 Description of AFCS Keys Located on the MFD 7 79 Other Controls Associated with the AFCS 7 82 Standby Instruments 7 84 Mid Continent Instrument 430...

Page 306: ...Terrain and Obstacle Clearance Requirements 7 89 RTC and ROC Cautions and Warnings 7 90 ITI and IOI Cautions and Warnings 7 91 PDA Premature Descent Alert TOO LOW TERRAIN 7 92 Excessive Descent Rate EDR Alert 7 93 Negative Climb Rate NCR After Takeoff Alert 7 94 Five Hundred Voice Alert 7 94 Geometric Altitude Display 7 94 Stormscope If Installed 7 95 Distance Measuring Equipment if installed 7 95...

Page 307: ...ts to be arranged in a forward facing posi tion FLIGHT CONTROLS CONTROL SURFACES Control surfaces are bearing supported and operated through push pull rods and conventional chain cable systems terminat ing in bellcranks CONTROL COLUMNS The airplane is equipped with dual control columns for the pilot and copilot The control wheels are interconnected and provide aileron and elevator control RUDDER P...

Page 308: ...pper flight navigation instrument panel and a lower subpanel The avionics circuit breaker panel is located below the lower right subpanel and the electrical circuit breaker panel is on the side panel to the left of the pilot s seat FLIGHT NAVIGATIONAL INSTRUMENT PANEL The flight navigation instrument panel is equipped with elec tronic displays an audio panel and standby flight instruments The elec...

Page 309: ...aker panel is on the side panel to the left of the pilot s seat OAT GAGE TH 2125 THRU TH 2339 EXCEPT TH 2310 The OAT Outside Air Temperature gage is located on the left cabin side panel just aft of the instrument panel Its tempera ture sensing probe extends through the cabin sidewall into the outside air The indicated Outside Air Temperature IOAT shown on this gage varies with airspeed and must be...

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Page 311: ...Systems Description Section 7 Model G58 TYPICAL INSTRUMENT PANEL TH07C 081770AB AI 7 11 May 2015 ...

Page 312: ...Systems Description Model G58 Section 7 7 12 May 2015 ...

Page 313: ...Systems Description Section 7 Model G58 7 13 May 2015 ...

Page 314: ...D RELAY 1 5 30 5 3 7 5 10 CABIN LTS LDG GR POS LTS PROP SYNC LEFT BUS LEFT BUS 5 5 5 5 ANNUN LIGHTS SURFACE DEICE FLAP RELAY UTIL PWR FLAP MOTOR STALL WARN LDG GR WARN 5 5 5 5 15 QUARTZ MIC PHONE 0 0 9 1 1 1 10 HOURS Hobbs RIGHT FUEL BOOST PUMP LEFT CABIN HEATER 10 10 20 RIGHT LEFT START RELAY R ENG AFR SNSR HOUR METER 5 10 5 5 5 FLIGHT VENT AIR BLOWER 10 May 2015 ...

Page 315: ...l The switch must be pulled out of a detent to change flap position The flaps can be moved to any of the three positions from any previously selected position there are no intermediate positions Three flap position lights placarded IN TRANSIT red APH blue and DN amber are located immediately to the left of the flap switch All of the lights are extinguished when the flaps are in the UP position The...

Page 316: ... to approximately 15 in Hg manifold pressure or above Do not change the position of the control switch to reverse the direction of the land ing gear while the gear is in transit as this could cause damage to the retract mecha nism POSITION LIGHTS Landing gear position lights are located above the control switch Three green lights forming a triangle to represent the individual gears are illuminated...

Page 317: ...t least one throttle above approximately 15 in Hg manifold pressure may allow the gear struts to extend momen tarily closing the circuit long enough to begin retraction NEVER RELY ON THE SAFETY SWITCHES TO KEEP THE GEAR DOWN DURING GROUND MANEUVERING CHECK TO SEE THAT THE LANDING GEAR HANDLE IS DOWN WARNING HORN AND GEAR UP ANNUNCIA TION With the landing gear retracted a warning horn will sound in...

Page 318: ...eaker before manually extending the gear When the electrical system is operative the landing gear may be checked for full down with the gear position lights provided the landing gear RELAY circuit breaker is engaged After the landing gear is down disengage the handcrank For electrical retraction of the landing gear after a practice manual extension use the procedures outlined in Section 3A ABNORMA...

Page 319: ... pressures The brake hydraulic fluid reservoir is accessible through the nose baggage door Fluid level is checked with the dipstick attached to the reservoir cap The brakes require no adjust ments since the pistons move outward to compensate for lin ing wear BAGGAGE COMPARTMENTS AFT BAGGAGE COMPARTMENT The aft baggage compartment is accessible through the utility doors on the right side of the fus...

Page 320: ...and any equipment which may be installed The nose baggage compartment incor porates the full width of the fuselage as usable space Straps are provided and should be used to secure any baggage loaded into the compartment SEATS The front two seats are adjustable as follows Forward and Aft Pull up on the release bar located below the forward left side of the seat and slide the seat to the desired pos...

Page 321: ...lded down by releasing the handle located on the aft inboard side of each seat The Aft two seats are adjustable as follows The seat backs can be folded down to provide access to the extended baggage compartment The seat cushions can be folded up to provide additional floor space Outboard armrests for all seats are built into the cabin side walls Center armrests of the front two seat and the middle...

Page 322: ...op stowed in one of the outer tracks For Forward facing Seats 3 One stop in the only hole in each outer track for conve nience install these stops prior to installation of seats 4 One stop in the most forward available hole of the center track NOTE When installing the seats ensure that the armrests are toward the center of the air plane SEAT CHANGE SCHEMATIC May 2015 ...

Page 323: ...tial reel is designed with a locking device that will secure the harness in the event of sudden forward movement or an impact action When using the shoulder harness the limitations stated on the cabin window placards must be observed Each shoulder harness is worn over the shoulder and down across the body where it is fastened by a metal loop into the seat belt buckle For the pilot seats the harnes...

Page 324: ...andle is in the open position In this position the latch handle is free to move approximately one inch in either direction before engagement of the locking mechanism Grasp the door and firmly pull the door closed Rotate the door handle fully counterclockwise into the locked position Observe that the door handle indicator is in the CLOSED position When the door is properly locked the door latch han...

Page 325: ...ed it can be latched from the outside by rotating the half moon shaped handle to the CLOSED position A conventional handle on the inside of this door provides for opening or closing from the inside The AFT DOOR amber caution alert will be displayed in the annunciation window of the PFD and remain until the doors are properly latched The ALERTS SOFTKEY in the lower right of the PFD will change to a...

Page 326: ...D position 2 Lift thumb catch window will release 3 Push latch up and outward to over center position To close window 1 Pull latch inward and push down until locked listen for catch engagement 2 Rotate lock handle to LOCKED position To operate the window as an emergency exit 1 Remove Emergency Exit Latch Cover 2 Rotate exposed red handle up breaking safely wire and push window out NOTE Anytime the...

Page 327: ...he hole pro vided in the collar lock and into the hole in the control column Push pin through hole as far as possible 3 Rotate control lock hanger over control column so inter connecting cable is to the right of control column 4 Assure positive retention of the lock pin by checking for movement in the control wheel 5 Position pilot s rudder pedals in aft position and install spring lock between pe...

Page 328: ...cription Model G58 Section 7 7 28 The control column lock assembly is placarded with the instal lation instructions The placard reads On Instruction Side On Side Facing Pilot with Locks Properly Installed May 2015 ...

Page 329: ...on the levers are shaped to standard FAA configuration so they can be identified by touch The controls are centrally located for ease of operation from either the pilot s or the copilot s seat An adjustable friction knob located on the right side of the pedestal is provided to prevent creeping of the control levers INDUCTION AIR Induction air is available from filtered ram air or unfiltered alter ...

Page 330: ...filter and has a 12 quart capacity Oil operating temperatures are controlled by an automatic thermostat bypass control The bypass control will limit oil flow through the oil cooler when operating tempera tures are below normal and will permit the oil to bypass the cooler if it should become blocked The oil system may be checked through access doors in the engine cowling A calibrated dipstick attac...

Page 331: ...artzell constant speed variable pitch three blade aluminum hub aluminum blade model PHC J3YF 2UF FC7391D K propellers the K in the propeller blade designates that the propeller is equipped with electro thermal deice Maximum diameter allowed is 75 inches Minimum diameter allowed is 73 inches The pitch set ting at the 30 inch station is 12 8 0 2 low pitch 18 5 1 0 high pitch and 80 0 0 5 feathered A...

Page 332: ...erts any pulse rate differences into correction commands which are transmitted to the appropriate governor A toggle switch installed on the pilot s subpanel turns the sys tem on To operate the system manually synchronize the pro pellers and then turn the PROP SYNC switch ON To change RPM adjust both propeller controls at the same time This will keep the setting within the limiting range of the sys...

Page 333: ...cent to each filler cap indicates fuel capacity and usable fuel when that wing fuel system is full Refer to Section 2 LIMITATIONS for usable fuel in each system A vapor return line returns excess fuel from the engine to its respective wing system All of the fuel cells standard or optional in each wing are interconnected in order to make all the usable fuel in each wing available to its engine when...

Page 334: ...t time has been allotted for any contaminants to settle into the sumps If inspections are made immediately after the airplane has been moved or refueled contaminants may be flushed from the sump or newly added contaminants may not have had time to settle into the sumps Sampling should be conducted with the airplane parked on level ground Check fuel for the proper grade type and absence of water di...

Page 335: ... line rotates in proportion to the fuel flow The speed of rotation is converted to an electrical signal which is then interpreted by the left and right GEA units The green band indicates the nor mal operating range while the red radial bands indicates the maximum allowable fuel flow A placard on the instrument panel notes the need for manual leaning During a climb a cyan climb fuel flow marker wil...

Page 336: ...ISTRIBUTOR ENGINE DRIVEN PUMP CHECK VALVE VENT LINE CHECK VALVE SIPHON BREAK PRESSURE RELIEF VALVE EXTERNAL VENT HEATED BOX SECTION CELL FUEL RETURN LINE FILLER CAP WING TIP FUEL TANK DRAIN DRAIN DRAIN AUX FUEL PUMP STRAINER CROSSFEED FUEL SELECTOR VALVE FUEL SELECTORS HEATER FUEL PUMP WITH FUEL FILTER HEATER HEATER FUEL LINE FROM LEFT FUEL CELL ONLY FUEL RETURN FUEL LINE FUEL SUPPLY VENT LINE MEC...

Page 337: ...BUTOR ENGINE DRIVEN PUMP TRANSMITTER BOTTOM MOUNTED VENT LINE CHECK VALVE SIPHON BREAK CHECK VALVE PRESSURE RELIEF VALVE EXTERNAL VENT HEATED BOX SECTION CELL FUEL RETURN LINE FILLER CAP DRAIN DRAIN AUX FUEL PUMP STRAINER CROSSFEED FUEL SELECTOR VALVE FUEL SELECTORS HEATER FUEL PUMP WITH FUEL FILTER HEATER HEATER FUEL LINE FROM LEFT FUEL CELL ONLY TH07C 051006AA AI FUEL RETURN FUEL LINE FUEL SUPPL...

Page 338: ...itions The system cannot transfer fuel from one wing system to the other The procedure for using the cross feed system is described in Section 3 EMERGENCY PROCE DURES ENGINE DRIVEN FUEL PUMPS The IO 550 C engines are equipped with engine driven fuel pumps that require manual leaning FUEL BOOST PUMPS The fuel boost pumps are dual speed dual pressure electri cally driven vane type pumps HI pressure ...

Page 339: ...t the fuel quantity indicators are functioning and maintaining a reasonable degree of accuracy and be certain of ample fuel for a flight A minimum of 13 gallons of fuel is required in each wing system before takeoff ELECTRICAL SYSTEM POWER SOURCES Refer to the Electrical Schematic Diagram and Left and Right Avionics Electrical Equipment Bus Connection Tables The airplane electrical system is a 28 ...

Page 340: ...hed to the back of the standby attitude indicator If power is lost to the right bus or to the L CB PANEL BUS powered by the Right Bus this battery will power the standby attitude indicator for a minimum of one hour if the battery is fully charged PROTECTIVE DEVICES The electrical system is protected by current limiters circuit breakers and circuit breaker type switches A row of re setta ble circui...

Page 341: ...am The bus titles denote the loca tion in the cockpit where the associated protection device is located the Avionics Circuit Breaker Panel the Left Circuit Breaker Panel and the circuit breaker type switches located on the Pilot s Instrument Subpanel The LEFT and RIGHT AVI ONICS ELECTRICAL EQUIPMENT BUS CONNECTION tables show the location of each piece of electrically powered equipment in relation...

Page 342: ... Tie system include the following 1 With both alternators inoperative and one or both batter ies selected on placing either alternator switch to the BUS TIE position will close the Bus Tie relay If both bat teries are on the left and right bus voltage will be the average of the two battery voltages 2 The Bus Tie relay is automatically closed when the External Power relay is closed and external pow...

Page 343: ... BATTERY RIGHT ALTERNATOR PILOT SUBPANEL 80A 35A 100A 100A 100A L CB PNL AVIONICS CB PNL EXT POWER AVIONICS RELAY BUS TIE RELAY SHUNT HOT BAT BUS ALT RELAY RIGHT BUS 35A GEA BUS VOLTS GEA LEFT ALT LOAD BATTERY RELAY START CONTROL RELAY LEFT START LEFT BATTERY LEFT ALTERNATOR L CB PANEL 35A AVIONICS CB PNL 60A 100A 100A 100A SYMBOLS CURRENT LIMITER PILOT SUBPANEL SHUNT ALT RELAY LEFT BUS May 2015 ...

Page 344: ...em Refer to the Electrical Schematic Diagram LEFT BUS L BUS System Avionics Circuit Breaker Panel Left Circuit Breaker Panel Pilot s Subpanel Circuit Breaker Switches Avionics ADC AHRS COMM 1 INTEG AVION 1 L ENG AFR SENSOR PFD PFD FAN XPNDR Engine START RELAY LEFT FUEL BOOST PUMP LEFT Environmental AIR COND opt AIR COND BLOWER opt VENT AIR BLOWER Landing Gear LDG GR POS LTS May 2015 ...

Page 345: ...em Avionics Circuit Breaker Panel Left Circuit Breaker Panel Pilot s Subpanel Circuit Breaker Switches Lights CABIN LIGHTS BCN ICE LDG FLOOD STROBE Icing FUEL VENT PITOT HEAT L PROP STALL WARN HEAT LEFT AVIONICS ELECTRICAL EQUIPMENT BUS CONNECTION Continued May 2015 ...

Page 346: ...al Schematic Diagram RIGHT BUS R BUS System Avionics Circuit Breaker Panel Left Circuit Breaker Panel Pilot s Subpanel Circuit Breaker Switches Avionics AP SERVOS AVIONICS MASTER AUDIO MKR CLOCK AVIONICS FAN R ENG AFR SNSR COMM 2 STBY HORIZ DATA LINK DME opt INTEG AVION 2 MFD RADAR STORM SCOPE opt TRAFFIC ALERT opt Electrical UTIL PWR items in this column are controlled by the avionics master swit...

Page 347: ...witches Engine HOUR METER PROP SYNC START RELAY RIGHT Environmental CABIN HEATER Flight Controls FLAP RELAY FLAP MOTOR Fuel FUEL BOOST PUMP RIGHT Landing Gear LANDING GEAR RELAY LANDING GEAR MOTOR Lights PANEL NAV LDG TAXI Warning ANNUN LIGHTS LDG GR WARN STALL WARN Icing SURFACE DEICE WSHLD RIGHT AVIONICS ELECTRICAL EQUIPMENT BUS CONNECTION Continued May 2015 ...

Page 348: ...e of the MFD Numerical values for alternator loads ALT LOAD L and ALT LOAD R and bus volt ages BUS VOLTS L and BUS VOLTS R are available by pressing the ENGINE softkey then the SYSTEM softkey on the MFD to access the ENGINE SYSTEM page In the event the MFD is not operational the engine default page will be positioned along the left side of the PFD The Engine System page may also be selected on the...

Page 349: ...nator Load High Caution amber ALT LOAD Left or Right Alternator load exceeds 100 amps Left Voltage Regulator Inoperative Caution amber LBUS VOLT HI Left bus voltage greater than 30 VDC Right Voltage Regulator Inoperative Caution amber RBUS VOLT HI Right bus voltage greater than 30 VDC Left Bus Voltage Low Caution amber LBUS VOLT LO Left bus voltage less than 24 VDC Suppressed below 500 RPM Right B...

Page 350: ...certain that the battery switches are ON all avionics and electrical switches OFF and the batteries are in the system before connecting an external power unit This protects the electronic voltage regula tors and associated electrical equipment from voltage tran sients power fluctuations If polarity is reversed a diode in the coil circuit will prevent contactor operation The Bus Tie relay closes au...

Page 351: ...Flaps Post Light Prop Deice Ammeter Standby Airspeed Indicator Standby Altimeter Standby Attitude Indicator SUBPANEL LIGHTING rheostat Adjusts the lighting intensity of the electroluminescent subpanels and circuit breaker pan els The map compass and OAT indicator lights are controlled by a push on push off switch located on the pilot s control wheel Cabin reading lights are located above each seat...

Page 352: ...g ground maneuvering which could cause overheating The nose gear taxi light should be used during ground operation NOTE Particularly at night reflections from anti collision lights on clouds dense haze or dust can produce optical illusions and intense vertigo Such lights when installed should be turned off before entering an overcast their use may not be advisable under instrument or limited VFR c...

Page 353: ...anding gear is retracted and automatically turn back on when the landing gear is extended BLOWER switch This switch also turns the heater blower on It may be used independent of heater operation to increase air circulation during ground operations If the heater blower is activated by this switch it will automatically turn off when the landing gear is retracted and automatically turn back on when t...

Page 354: ...essure switch which removes power from the ignition system and the heater fuel pump if the heater blower or combustion air blower fails The distribution of the heated air is controlled by the following controls 1 Pilot Air control knob This knob is located below the pilot s subpanel Pulling the knob out increases the air flow at the pilot s feet 2 Copilot Air control knob This knob is located belo...

Page 355: ...Systems Description Section 7 Model G58 7 55 ENVIRONMENTAL SCHEMATIC May 2015 ...

Page 356: ...ations The blower becomes inoperative when the landing gear is retracted INDIVIDUAL OVERHEAD FRESH AIR OUTLETS Fresh ram air from the intake on the left side of the dorsal fair ing is ducted to individual outlets above each seat including the optional fifth and sixth seats A master control in the over head panel just aft of the front air outlets enables the pilot to adjust the amount of ram air av...

Page 357: ...of static air to the ADC standby airspeed indicator and standby altimeter for operation through a flush static fitting on each side of the air plane fuselage EMERGENCY STATIC AIR SYSTEM The emergency static air system is installed to provide air to the ADC standby airspeed indicator and standby altimeter for operation should the static ports become blocked The emer gency air source control is loca...

Page 358: ...Systems Description Model G58 Section 7 7 58 PITOT AND STATIC SYSTEM SCHEMATIC E 07C 052872AA AI EMERGENCY STATIC SOURCE PITOT MAST DRAIN DATA BUS ADC MFD STBY A S PFD STBY ALT STATIC SOURCE May 2015 ...

Page 359: ...EDURES A switch on the left subpanel placarded STALL WARN HEAT controls electrical power to the stall warning heater elements ICE PROTECTION SYSTEMS SURFACE DEICE SYSTEM Deice boots cemented to the leading edges of the wings hori zontal tail surfaces and vertical tail surface are operated by engine driven pump pressure Compressed air after passing through the pressure regulators goes to the distri...

Page 360: ...ion of the surface deice system in ambient temperatures below 40 C can cause permanent damage to the deice boots The wing ice light used to check for ice accumulation during night operation is located on the outboard side of the left nacelle The light switch is on the pilot s subpanel ELECTROTHERMAL HEATED WINDSHIELD SEGMENT The pilot s electrically heated windshield segment is controlled by a swi...

Page 361: ...ght it will function automatically until the switch is turned off Propeller imbalance can be relieved by varying RPM Increase RPM briefly then return to the desired setting Repeat if necessary Do not operate the system with the engines inoperative PITOT HEAT A heating element is installed in the pitot mast The heating element is controlled by a switch located on the pilot s sub panel The switch is...

Page 362: ...5 hours If addi tional oil is needed during the first 25 hours of operation use an approved straight mineral oil per MIL L 6082 If oil con sumption has not stabilized by this time the engine should be drained and refilled with MIL L 6082 Mineral Oil This oil should be used until oil consumption stabilizes usually a total of approximately 50 hours After oil consumption has stabi lized MIL L 22851 A...

Page 363: ...perating conditions are unusually dusty and dirty more frequent oil changes may be necessary Oil changes are more critical dur ing break in period than at any other time Use full throttle for every takeoff and maintain until at least 400 feet AGL then reduce power as necessary for cruise climb Maintain the highest power recommended for cruise operation during the break in period 50 to 75 hrs and i...

Page 364: ...ions transceivers dual VOR ILS receivers and dual GPS receivers A single Transponder A single Magnetometer A Flight Director Autopilot System that is integral to the GIA and the autopilot servo units PRIMARY FLIGHT DISPLAY PFD The Primary Flight Display PFD is a 10 4 inch Liquid Crystal Display LCD referred to by Garmin as a Garmin Display Unit GDU 1040 It displays airspeed attitude altitude and h...

Page 365: ...nd is protected by a circuit breaker placarded PFD located on the avionics circuit breaker panel See the Garmin G1000 Primary Flight Display Pilot s Guide for more detailed information MULTIFUNCTION DISPLAY MFD The Multi Function Display MFD is a 10 4 inch Liquid Crystal Display LCD referred to by Garmin as a Garmin Display Unit GDU 1043 1045 It displays engine data maps terrain traffic and topogr...

Page 366: ...ived COMM audio A marker beacon receiver is also contained within the audio panel with visual information provided on the PFD The red button at the bottom of the audio panel is used to manually select the reversionary mode for the PFD and MFD displays The GMA is powered by the Right Bus through the Avionics Master relay and is pro tected by the 5 amp AUDIO MKR circuit breaker located on the Avioni...

Page 367: ...ted by the 5 amp ADC circuit breaker located on the Avionics Circuit Breaker Panel See pitot and static system description in this section for more detailed information MAGNETOMETER GMU The Garmin Magnetometer Unit GMU 44 senses the Earth s magnetic field and provides this information to the AHRS for processing to determine the airplane s magnetic heading The GMU 44 is located in the left wing tip...

Page 368: ...re MAP Engines RPM Fuel Flow Six Cylinder Head Temperature CHT probes Six Exhaust Gas Temperature EGT probes Oil Temperature Oil Pressure Left Alternator Load Right Alternator Load Left Bus Voltage Right Bus Voltage Fuel Quantity Left Tank Fuel Quantity Right Tank Starter Engaged Utility Door Switch Left GEA 71 Air Conditioning Condenser position Left GEA 71 This information is used to display Eng...

Page 369: ...rating transponder Transponder codes and mode selection are accessed by the XPDR softkey at the bottom of the PFD Squawk codes can be entered using the PFD FMS knob software version 0857 05 or 0857 06 The GTX 33 is powered by the Left Bus and protected by a 5 amp circuit breaker located on the Avionics Circuit Breaker Panel AIRBORNE WEATHER RADAR GWX The Garmin Airborne Weather Radar GWX 68 provid...

Page 370: ...anifold pressure limits as indicated on the Manifold Pressure vs RPM graph in Section 5 PERFORMANCE The left and right circular scale with a pointer provides overall engine speed in revolutions per minute RPM with numeric value just below A transducer attached to each engine sends electrical signals to the left and right GEA units for display information Fuel flow is indicated on a linear scale wi...

Page 371: ...he Garmin G1000 Engine Indication System Pilot s guide for more detailed information ALERTING SYSTEM The G1000 provides an Annunciation window and an Alerts window on the PFD to inform the pilots of Warning Alerts Cau tions Alerts Advisory Alerts and Messages that may occur during the operation of the airplane Both windows are also available on the MFD to provide the same notifications when the MF...

Page 372: ... cancel the flashing mode of the softkey When an alert is acknowledged the annunciation is moved to the top portion of the Annunciation Window and is separated from subsequent annunciations that may occur by a white line If more than one annunciation is displayed they are arranged in order of priority with the highest priority at the top of the list Thus they would be arranged from top to bottom i...

Page 373: ...t Alerts Softkey Tone Warning Alert CHT HI L or R CHT is greater than 238 C WARNING Repeating Warning Alert FUEL FLOW HI L or R fuel flow is greater than 27 4 gph WARNING Repeating Warning Alert FUEL QTY LO L or R fuel qty is at zero WARNING Repeating Warning Alert GEAR UP Gear Up WARNING Cont Warning Alert L R ALT INOP Left and Right alternator offline WARNING Repeating Warning Alert L ALT INOP L...

Page 374: ...e Caution Alert LBUS VOLT LO Left Bus voltage Less than 24 VDC CAUTION Single Caution Alert RBUS VOLT HI Right Bus voltage greater than 30 VDC CAUTION Single Caution Alert RBUS VOLT LO Right Bus voltage Less than 24 VDC CAUTION Single Caution Alert OIL PRESS LO L or R oil press is between 30 and 10 psi CAUTION Single Message AVIONICS FAN Cooling fan for remote avionics is inoperative ADVISORY None...

Page 375: ...s If Installed i VS Vertical Speed Mode On Off j FLC Flight Level Change Mode On Off k NOSE UP and NOSE DN vertical mode reference change 2 A two segment pitch trim switch located on the left side of the pilot s control wheel 3 A red autopilot disconnect and pitch trim interrupt switch AP DISC TRIM INTER located on the left side of the pilot s control wheel Pressing this switch also acknowl edges ...

Page 376: ...ted on the Avi onics circuit breaker panel Both GIAs are required to be operational for the AFCS to operate 9 The AFCS also utilizes the PFD MFD mounted altitude preselect knob ALT heading select knob HDG and course select knob CRS associated with the G1000 system PFD DISPLAYS 1 A Flight Director command bar is displayed on the artifi cial horizon when the Flight Director is active 2 The status of...

Page 377: ...flight director and pitch trim systems to be operational If the Preflight Test fails a red PFT is dis played in the system status field If a failure occurs after the preflight test has been successfully passed a red AFCS will be displayed in the field If a failure of the electric pitch trim system occurs a red PTRM will be displayed in the field 4 OVERSPEED PROTECTION MAXSPD If the indi cated airs...

Page 378: ...few failures such as loss of power to the servos or turning the Avionics Switch off will also render the AP DISC switch inoperative In such cases the left side of the pitch trim switch will still cancel the disconnect tone and flashing annunciator The following conditions will cause the autopilot and in the first six cases the yaw damp to disengage 1 AFCS electrical power failure including pulling...

Page 379: ...e autopilot When the yaw damper is engaged the green YD will illuminate in the AFCS Status Bar FD Flight Director Engages and disengages the Flight Director if the autopilot is not engaged When the flight director is engaged the green ROLL PIT and white ALT will illumi nate in the AFCS Status Bar HDG Heading Mode Engages and disengages the Heading Mode The Flight Director will maintain the heading...

Page 380: ...is used to track the fol lowing types of approaches 1 ILS approaches LOC and GS 2 GPS non precision approaches Tracking accuracy will be identical to the NAV Mode GPS 3 VOR non precision approaches VAPP WAAS Software Version 0857 05 or 0857 06 4 LPV approach with lateral and vertical guidance GPS and GP 5 LNAV VNAV approach with lateral and vertical guidance GPS and GP When the Approach mode is se...

Page 381: ...interception the selected altitude must be set below the current airplane alti tude One minute prior to the top of descent TOD the mes sage TOD within 1 minute displays in the PFD Navigation Status Box accompanied by the Vertical Track voice mes sage VNV indications target altitude vertical deviation speed required appear on the PFD in magenta When the vertical profile is captured green VPTH becom...

Page 382: ...SE DN key increases the air speed by 1 knot When the Flight Level Change mode is selected the green FLC and the current airspeed XXXKT are displayed in the AFCS Status Bar In addition the selected airspeed is dis played in a box above the airspeed indicator and a reference bug is displayed on the right side of the airspeed Display NOSE UP NOSE DN Keys Used to adjust the pitch in the pitch mode PIT...

Page 383: ...ing upon the mode selected If the autopilot and flight director have not previously been engaged pressing the CWS button will activate the flight director in the pitch and roll hold modes When the CWS mode is active a white CWS replaces the green AP in the AFCS status bar MANUAL ELECTRIC PITCH TRIM When the autopilot is not engaged the electric pitch trim system may be operated with the split trim...

Page 384: ...wer is supplied from the standby battery when Right Bus voltage reaches 10 volts The standby attitude indi cator is usable through 360 of pitch and roll The standby attitude indicator includes the following items 1 A mechanical red gyro warning flag which is displayed when the gyro motor is not receiving sufficient power to operate 2 A Pull To Cage Knob This knob will not lock the gyro After allow...

Page 385: ...d to the back of the indicator The battery will power the indicator for a minimum of one hour if fully charged when power is lost from Bus 1 and the pilot subsequently latches it on by pressing the STBY PWR button This battery must be removed and checked once a year and replaced every 3 years 7 Emergency LED lighting provided when the indicator is operating from standby battery This lighting is no...

Page 386: ...ectrical system except for lighting Lighting is provided by the Right Bus and is controlled by the STANDBY INST rheostat located on the right subpanel STANDBY COMPASS MAGNETIC COMPASS The standby compass is a self contained non stabilized com pass that will provide magnetic heading should the electric heading reference fail from the Attitude and Heading Refer ence System AHRS or become unavailable...

Page 387: ...ing potential traffic conflicts within an 11 nautical mile range Aural traffic alerts are annunciated through the airplane audio sys tem and visual targets are displayed on the MFD It tracks up to 30 intruder airplane simultaneously and displays eight of the most threatening The system is on anytime the Avionics Master Switch is on and the TRAFFIC ADVISORY circuit breaker is in The system can be p...

Page 388: ...ired Terrain RTC and Obstacle ROC clearance cautions and warnings b Imminent Terrain ITI and Obstacle IOI Impact cau tions and warnings 2 Premature Descent Alerts PDA 3 The following basic Ground Proximity Warning System GPWS functions a Excessive Descent Rate EDR Alert b Negative Climb Rate NCR After Takeoff Alert c Five Hundred Aural Alert The TAWS functions FLTA and PDA may be inhibited by sele...

Page 389: ...rements allows for the normal loss of altitude that occurs as the airplane arrives at the desti nation This prevents nuisance cautions and warnings that may otherwise be received All alerts are automatically inhib ited when the airplane is below 200 feet AGL and within 0 5 nm of the runway or is below 125 feet AGL and within 1 nm of the runway The following table shows how the minimum terrain obst...

Page 390: ... the TAWS will provide voice warning alerts and annunciators as shown in the following table when it predicts that the airplane flight path will violate the minimum clearance requirements within 30 seconds DISTANCE FROM DESTINATION MINIMUM CLEARANCE REQUIREMENTS LEVEL FLIGHT DESCENDING 15 nm 700 ft 500 ft 5 to 15 nm 350 ft 300 ft 5 nm or less 150 ft 100 ft On departure 100 ft 100 ft REASON PFD MFD...

Page 391: ...in or obstacle within 30 seconds REASON PFD MFD TAWS PAGE ANNUNCIATOR RED MFD POP UP ANNUNCIATOR RED VOICE CAUTION ALERT Violation of Required Terrain Clearance RTC Requirements PULL UP TERRAIN PULL UP Terrain Ahead Terrain Ahead Violation of Required Obstacle Clearance ROC Requirements PULL UP OBSTACLE PULL UP Obstacle Ahead Obstacle Ahead In addition potential impact point s are depicted by red ...

Page 392: ...L UP OBSTACLE PULL UP Obstacle Ahead Pull Up Obstacle Ahead Pull Up In addition potential impact point s are depicted by red Xs on the TAWS page TYPE OF APPROACH ALERT BOUNDARY CAUSE FOR THE ALERT BEGINNING END Visual Approach No approach Loaded Airplane is 15 nm from the destination airport 0 5 nm from the runway threshold OR when within 1 nm and at 125 AGL or below Airplane descends below establ...

Page 393: ...iators will be provided as shown in the table below If corrective action is not taken to correct the excessive descent rate or the descent rate increases the system will provide a voice warning alert and annunciators as shown in the table below PFD MFD TAWS PAGE ANNUNCIATOR YELLOW MFD POP UP ANNUNCIATOR YELLOW VOICE ALERT TERRAIN TOO LOW TERRAIN Too Low Terrain PFD MFD TAWS PAGE ANNUNCIATOR YELLOW...

Page 394: ...t is provided during a descent when the airplane reaches 500 feet above the terrain There are no associated annunciators The alert is enabled during the climb when the airplane s altitude exceeds 675 feet AGL and is disabled after the alert is provided at 500 feet AGL during a descent GEOMETRIC ALTITUDE DISPLAY This is the airplanes altitude above Mean Sea Level and is cal culated by the TAWS B sy...

Page 395: ... ered by the Right Bus through the Avionics Master rely and is protected by a 3 amp circuit breaker placarded STORM SCOPE located on the Avionics Circuit Breaker Panel The WX 500 stormscope displays lightning information directly on the MFD either on a dedicated page or overlaid on the moving map The WX 500 stormscope operates in the Strike and Cell mode and is controlled through the MFD panel Mom...

Page 396: ...e lage area an antenna mounted on the aft fuselage and a remote switch with a red transmit light usually located on the right side of the instrument panel Neither the remote switch nor the switch on the ELT transmitter can be positioned to pre vent the automatic activation of the ELT transmitter The sys tem is independent from other airplane systems except for the transmit light which is hot wired...

Page 397: ...ch to ON Wait for at least 3 sweeping tones on the airplane radio which will take about 1 second then return the switch to ARM The test is successful if the sweeping tones are heard and the transmit light next to the switch blinks immedi ately If there is a delay in the illumination of the transmit light the system is not working properly If the ELT should be inadvertently activated by the G switc...

Page 398: ...Systems Description Model G58 Section 7 7 98 THIS PAGE INTENTIONALLY LEFT BLANK May 2015 ...

Page 399: ... Repairs To The Airplane 8 8 Ground Handling 8 9 Towing 8 10 Parking 8 10 Tie Down 8 11 Main Wheel Jacking 8 11 Prolonged Out of Service Care 8 12 Storage 8 12 Flyable Storage 7 to 30 Days 8 12 Mooring 8 12 Engine Preparation For Storage 8 13 During Flyable Storage 8 13 Fuel Cells 8 13 Flight Control Surfaces 8 13 Grounding 8 14 Pitot Tube 8 14 Windshield and Windows 8 14 Preparation For Service 8...

Page 400: ...l System 8 17 Batteries 8 19 Tires 8 19 Shock Struts 8 20 Shimmy Damper 8 22 Brakes 8 23 Induction Air Filters 8 24 Propellers 8 24 Minor Maintenance 8 25 Rubber Seals 8 25 Heating and Ventilating System 8 25 Alternators 8 25 Magnetos 8 26 Cleaning 8 27 Exterior Painted Surfaces 8 27 Landing Gear 8 29 Windshield and Windows 8 30 Surface Deice Boots 8 30 Engine 8 31 Interior 8 31 ...

Page 401: ...Model G58 8 3 April 2008 SECTION 8 HANDLING SERV MAINT TABLE OF CONTENTS SUBJECT PAGE Consumable Materials 8 32 Approved Engine Oils 8 33 Lamp Replacement Guide 8 34 ...

Page 402: ...Model G58 8 4 April 2008 Section 8 Handling Servicing and Maint THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 403: ...ne by qualified mechanics in conformity with all airworthiness requirements established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized Hawker Beechcraft Corporation outlets can provide recommended modification service and operating procedures issued by both FAA and Hawker Bee...

Page 404: ...s and revisions of FAA Approved Airplane Flight Manual Supplements 3 Original issues and revisions of Hawker Beechcraft Cor poration Service Bulletins The above publications will be provided only to the owner and or operator at the address listed on the FAA Aircraft Registra tion Branch List or the Hawker Beechcraft Corporation Domes tic International Owner s Notification Service List Further the ...

Page 405: ...ules NOTE In event of any gear or flap extension at speeds above the respective normal exten sion speeds inspect gear retract rods gear doors and flaps for damage or distortion before the next flight PREVENTATIVE MAINTENANCE THAT MAY BE ACCOMPLISHED BY A CERTIFICATED PILOT 1 A certificated pilot may perform limited maintenance Refer to 14 CFR Part 43 for the items which may be accomplished NOTE To...

Page 406: ...made by properly licensed personnel Use only genuine Hawker Beechcraft Cor poration or Hawker Beechcraft Corporation approved parts obtained from Hawker Beechcraft Corporation approved sources in connection with the maintenance and repair of Beechcraft airplanes Genuine Hawker Beechcraft Corporation parts are produced and inspected under rigorous procedures to ensure airworthi ness and suitability...

Page 407: ...ive testing techniques This may render the part component or structural assembly even though originally manufactured by Hawker Beechcraft Cor poration unsuitable and unsafe for airplane use Hawker Beechcraft Corporation expressly disclaims any responsibility for malfunctions failures damage or injury caused by use of non Hawker Beechcraft Corporation approved parts GROUND HANDLING The three view d...

Page 408: ...own ring Do not tow when the main gear is obstructed by mud or snow Also ensure the rudder lock is removed Care should be used when removing the tow bar to prevent damage to the lubrication fittings on the landing gear PARKING The parking brake control is located just left of the elevator tab wheel on the pilot s subpanel To set the parking brakes pull control out and depress each toe pedal until ...

Page 409: ... attack of the wings 4 Release the parking brake If high winds are anticipated a vertical tail post should be installed at the rear tie down lug and a tie down line attached to the nose gear MAIN WHEEL JACKING Individual main wheels may be jacked by placing a floor jack under the jacking point located under each axle Prior to jacking the airplane ensure that an unbalanced fuel condition does not e...

Page 410: ...protect the air plane from deterioration while it is not in use The primary objectives of these measures are to prevent corrosion and damage from exposure to the elements Flyable Storage 7 to 30 days has been considered here For more extended storage periods consult the Beech Baron Shop Manual and Continental Service Bulletin M81 3 or later issue FLYABLE STORAGE 7 TO 30 DAYS MOORING Place the airp...

Page 411: ...s are OFF throt tles are in the CLOSED position and mixture controls are in the CUT OFF posi tion Always stand in the clear while turning the propellers Each seven days during flyable storage the propellers should be rotated by hand After rotating the engine six revolutions stop the propeller 60 to 120 from the position they were in If at the end of 30 days the airplane has not been removed from s...

Page 412: ...ing any external power source to avoid reversed polarity An external power unit APU should be capable of delivering at least 300 amperes for starting Serviceable batteries must be installed in the airplane Starting with external power when the battery is dead is not recommended The battery manufac turer warns against this also the battery will not recharge suf ficiently for use if an emergency ari...

Page 413: ...ical equipment connected to the unit may be damaged SERVICING FUEL SYSTEM FUEL CELLS See the Baron Maintenance Manual for recommended fuel grades The standard 200 gallon capacity fuel system has a fuel filler cap in each wing box section and each wet wing tip and in each outboard wing leading edge The optional 172 gallon capacity system has a filler cap in each outboard wing leading edge Refer to ...

Page 414: ... If the cells are to be drained before storage a coating of light engine oil should be sprayed or flushed onto the inner lin ers of the cells as a preservative NOTE The 200 gallon fuel system should be filled from the wing leading edge filler cap when airplane must stand for several days Check and fill to capacity at wet wing tip filler cap before flight if required for the mis sion The fuel fille...

Page 415: ...ing edge sump strainer accessible through an access door on the bottom of the wing should be cleaned periodically OIL SYSTEM The engines are equipped with a wet sump pressure type oil system Each engine sump has a capacity of 12 quarts The oil system may be serviced through access doors in the engine cowling A calibrated dipstick attached to the filler cap indi cates the oil level Due to the cante...

Page 416: ...PPROVED ENGINE OILS in this section for a list of approved oils Do not exceed 25 hours of operation with factory break in oil MIL C 6529 Type II Multi viscosity 20W 50 Corrosion preven tative When changing to MIL L 22851 Ashless Dispersant oil change the oil and oil filter as previously described Failure to remove the corrosion preventative oil and replace the oil filter within the time interval s...

Page 417: ...r to the Baron Maintenance Manual for battery mainte nance service instructions TIRES An inflation pressure of 52 to 56 psi should be maintained on the 6 50 x 8 main wheel tires The 5 00 x 5 nose wheel tire should be inflated to 55 60 psi Maintaining recommended tire inflation will minimize tread wear and aid in preventing tire fail ure caused from running over sharp stones and ruts When inflating...

Page 418: ...E While Hawker Beechcraft Corporation can not recommend the use of recapped tires tires retreaded by an FAA approved repair station with a specialized service limited rating in accordance with the latest revision of TSO C62 may be used SHOCK STRUTS DO NOT taxi with a flat shock strut The shock struts are filled with dry air or nitrogen and hydraulic fluid The same procedure is used for servicing b...

Page 419: ...ition NOTE Cycling of the shock strut is necessary to expel any trapped air within the strut hous ing 5 Install the air valve assembly 6 With the airplane resting on the ground and the fuel cells full inflate the nose gear strut until 3 1 2 to 3 3 4 inches of the piston are exposed and inflate the main gear struts until 3 inches of the piston are exposed Rock the air plane gently to prevent possib...

Page 420: ...ed in the pis ton rod Two coil springs installed in the piston rod keep fluid in the shimmy damper under pressure As fluid is lost through leakage it is automatically replenished from the reservoir until the reservoir supply is exhausted To check the fluid in the shimmy damper insert a wire approx imately 1 32 inch in diameter through the hole in the disc at the aft end of the piston rod until it ...

Page 421: ... the shimmy damper is found empty or nearly empty it should be refilled See Beech Baron Shop Manual BRAKES The brake hydraulic fluid reservoir is accessible through the nose baggage compartment A dipstick is attached to the res ervoir cap Refer to the Baron Maintenance Manual for hydrau lic fluid specification The brakes require no adjustments since the pistons move to compensate for lining wear T...

Page 422: ... noted by the manufac turer s instructions 3 Reinstall the filter and the plate PROPELLERS The daily preflight inspection should include a careful examina tion of the propeller blades for nicks and scratches Propeller operation servicing and maintenance instructions are contained in the propeller owner s manual furnished with the airplane When servicing a propeller always make certain that the ign...

Page 423: ... with molybdenum disulfide see the 55 58 G58 Baron Shop Manual The valve should never be lubricated with oil or any liquid lubricant which would collect dust Do not reset the overheat circuit breaker until a thorough inspection of the system has determined the cause and the malfunction has been corrected ALTERNATORS Since the alternator and electronic voltage regulator are designed for use on only...

Page 424: ...o the Baron Maintenance Manual for battery removal and charging procedures MAGNETOS Ordinarily the magnetos will require only occasional adjust ment lubrication and breaker point replacement This work should be done by a Hawker Beechcraft Corporation Autho rized Outlet To be safe treat the magnetos as hot whenever a switch lead is disconnected at any point they do not have an internal automatic gr...

Page 425: ...aning cover the wheels making certain the brake discs are covered Attach the pitot covers securely and plug or mask off all other openings Be particularly careful to mask off all static air buttons before washing or waxing Use special care to avoid removing lubricant from lubricated areas Hand washing may be accomplished by flushing away loose dirt with clean water then washing with a mild soap an...

Page 426: ...intenance Manual When using high pressure washing equipment keep the spray or stream clear of wheel bearings propeller hub bearings etc and openings such as pitot tubes static air buttons and bat tery and avionic equipment cooling ducts which should be securely covered or masked off Avoid directing high pressure sprays toward the fuselage wings and empennage from the rear where moisture and chemic...

Page 427: ...l deterioration of the characteristic urethane gloss For waxing select a high quality automotive or aircraft waxing product Do not use a wax containing silicones as silicone pol ishes are difficult to remove from surfaces A buildup of wax on any exterior paint finish will yellow with age therefore wax should be removed periodically Generally aliphatic naphtha see the Baron Maintenance Manual is ad...

Page 428: ...often the plastic and may cause it to craze After a thorough cleaning waxed the surface with a good grade of commercial wax that does not have an acrylic base The wax will fill in minor scratches and help prevent further scratching Apply a thin even coat of wax and bring it to a high polish by rubbing lightly with a clean dry soft flannel cloth Do not use a power buffer the heat generated by the b...

Page 429: ...ing tissue or rags Do not pat the spot press the blotting material firmly and hold it for several seconds Continue blotting until no more liq uid is taken up Scrape off sticky materials with a dull knife then spot clean the area Oily spots may be cleaned with household spot removers used sparingly Before using any solvent read the instructions on the container and test it on an obscure place on th...

Page 430: ...n the control wheel and control knobs can be removed with a cloth moist ened with isopropyl alcohol Volatile solvents such as men tioned in the article on care of plastic windows should never be used since they soften and craze the plastic CONSUMABLE MATERIALS For a complete list of Consumable Materials refer to the Baron Maintenance Manual April 2008 ...

Page 431: ... Aviation Multiviscosity SAE 20W50 X C Aviation Multiviscosity SAE 20W60 Quaker State Oil and Ref Quaker State AD Aviation Engine Oil Red Ram Ltd Canada Red Ram X C Aviation Oil 20W50 Shell Oil Co Aeroshell Oil W SAE 15W50 Aeroshell Oil W Sinclair Refining Co Sinclair Avoil Texaco Inc Texaco Aircraft Engine Oil Premium AD Union Oil of California Union Aircraft Engine Oil HD This chart lists all oi...

Page 432: ...ht 303 Compass Light 327 Flap Position Indicator Light 327 Ice Light A 7079B 24 Landing Gear Position Light 327 Landing Light 4596 Map Light WL41069R Navigational Light Tail w Strobe 34 0428070 64 Whelen Navigation Light Wing A7512 24 Grimes Nose Baggage Light 307 Reading Light 303 Step Light 1495 Tab Position Indicator Light 334 Taxi Light 4596 April 2008 ...

Page 433: ...whether it was installed or not Airplane Flight Manual Supplements for equipment for which the supplier obtained a Supplemental Type Certificate were included as loose equip ment with the airplane at the time of deliv ery These and other Airplane Flight Manual Supplements for other equipment that was installed after the airplane was delivered new for the factory should be placed in this section No...

Page 434: ...Supplements Model G58 Section 9 9 2 THIS PAGE INTENTIONALLY LEFT BLANK November 2005 ...

Page 435: ...02 77 Airplanes Registered in Brazil 1 Jul 2008 36 590002 89 Mode S Enhanced Surveil lance Transponder For Air planes Which Have Mode S Enhanced Surveillance Tran sponder Installed at the Fac tory Apr 2009 58 590000 73 Air Conditioning System 1 Jan 2007 58 590000 77 Airplanes Operating on the Argentine Register Non FAA Approved Dec 2007 58 590000 85 Airplanes Registered in Can ada Sep 2010 58 5900...

Page 436: ...in G1000 Air frame System Software Ver sion 0508 13 Oct 2008 190 01180 01 G1000 Avionics Upgrade with Synthetic Vision per STC SA01584WI D 2 May 29 2012 190 02128 03 Garmin G1000 NXi Integrated Avionics System and GFC 700 AFCS 1 Dec 20 2016 2033 AFMS S2 G58 Baron Millennium Con cepts Inc interior upgrade per STC SA01671WI IR Feb 3 2012 361601 Exterior LED Lighting Suite per STC SA02387AK IR Mar 8 ...

Page 437: ......

Page 438: ...Handbook and FAA Approved Airplane Flight Manual Supplement for Airplanes Registered in Brazil 2 of 6 P N 36 590002 77 REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 6 Original Issue Apr 2006 1 1 thru 6 Revised GPS Limitations and Reformatted Jul 2008 ...

Page 439: ...GENERAL This document is to be attached to the Pilot s Operating Hand book and FAA Approved Airplane Flight Manual for Airplanes registered in Brazil The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Flight Manual only as set forth within this document Users of the handbook are advised to always refer to the supplement for possibly super...

Page 440: ...ropriate to the route and phase of flight When continuing to use GPS navigation position must be veri fied every 15 minutes using other IFR approved naviga tion systems 3 If RAIM message is displayed in the terminal area or non precision approach phases of flight GPS based navigation should be reverted to another IFR approved navigation system 4 GPS SID s and STAR s IFR navigation is limited to cu...

Page 441: ...l operate only in areas with appro priate satellite coverage Satellite Based Augmentation System SBAS and integrated Wide Area Reference Stations WRS SECTION 3 EMERGENCY PROCEDURES No Change SECTION 3A ABNORMAL PROCEDURES No Change SECTION 4 NORMAL PROCEDURES No Change SECTION 5 PERFORMANCE No Change SECTION 6 WEIGHT AND BALANCE EQUIP MENT LIST No Change SECTION 7 SYSTEMS DESCRIPTION No Change SEC...

Page 442: ...6 of 6 THIS PAGE INTENTIONALLY LEFT BLANK FAA Approved on behalf of ANAC Revised July 2008 P N 36 590002 77 ...

Page 443: ......

Page 444: ...rating Handbook and FAA Approved Airplane Flight Manual Supplement for the Mode S Enhanced Surveillance Transponder For Airplanes Which Have Mode S Enhanced Surveillance Transponder Installed at the Factory 2 of 6 P N 36 590002 89 REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 6 Original Issue Apr 2009 ...

Page 445: ... information in this supplement is FAA approved material and must be attached to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is operated with Mode S Enhanced Surveillance Transponder in accordance with Hawker Beechcraft Corporation approved data SECTION 2 LIMITATIONS AVIONICS LIMITS MODE S ENHANCED SURVEILLANCE TRAN SPONDER The installed Mode S system s...

Page 446: ...ON 3A ABNORMAL PROCEDURES No change SECTION 4 NORMAL PROCEDURES No change SECTION 5 PERFORMANCE No change SECTION 6 WEIGHT AND BALANCE EQUIP MENT LIST No change Parameter Available Magnetic Heading Yes Indicated Airspeed Yes Mach No Yes Vertical Rate Yes Roll Angle Yes True Airspeed Yes True Track Angle Yes Groundspeed Yes Selected Altitude Yes Barometric Pressure Setting Yes ...

Page 447: ...FAA Approved Issued April 2009 5 of 6 P N 36 590002 89 SECTION 7 SYSTEMS DESCRIPTION No change SECTION 8 HANDLING SERVICING AND MAINTENANCE No change ...

Page 448: ...FAA Approved 6 of 6 P N 36 590002 89 Issued April 2009 THIS PAGE INTENTIONALLY LEFT BLANK ...

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Page 460: ...EVISIONS Model G58 Baron TH 2125 and After Pilot s Operating Handbook and TCCA Approved Airplane Flight Manual Supplement for Airplanes Registered in Canada REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 4 Original Issue Sept 2010 ...

Page 461: ...information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Flight Manual only as set forth within this document Users of the handbook are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane SECTION 2 LIMITATIONS AVIONICS GARMIN G1000 INTEGRATED AVIONICS SYSTEM Barometri...

Page 462: ...2010 SECTION 3 EMERGENCY PROCEDURES No change SECTION 3A ABNORMAL PROCEDURES No change SECTION 4 NORMAL PROCEDURES No change SECTION 5 PERFORMANCE No change SECTION 6 WT BAL EQUIP LIST No change SECTION 7 SYSTEMS DESCRIPTION No change SECTION 8 HANDLING SERV MAINT No change ...

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Page 464: ...Baron TH 2478 and After Pilot s Operating Handbook and Manufacturer Approved Airplane Flight Manual Supplement for Airplanes Equipped with A C Systems LLC Air Conditioning System REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 24 Original Issue Mar 2017 ...

Page 465: ...L The information in this supplement is FAA approved material and must be attached to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is equipped with the Automatic Climate Control System The Automatic Climate Control System incorporating an A C Systems LLC Air Conditioning System is designed to cool and heat the airplane cabin to desired temperature settin...

Page 466: ...nditioning Compressor Mode OFF NOTE This procedure ensures absolute maximum power is available for single engine opera tion ENGINE FIRE IN FLIGHT 1 Climate Control System OFF SYSTEM EMERGENCIES ELECTRICAL SMOKE OR FIRE 1 Climate Control System OFF SUSPECTED REFRIGERANT LEAK IN CABIN The Air Conditioning Compressor OFF mode on the Auto matic Climate Control should be selected by pressing the com pr...

Page 467: ...round Roll distance as published in the POH AFM for the applicable conditions by 4 and the corresponding Total Dis tance over a 50ft obstacle by 5 If this incremental distance is not available select the Compressor OFF mode during the takeoff portion of the flight by pressing the compressor switch button until the adjacent indicator light is out This selection is designed to ensure safe operation ...

Page 468: ...during the takeoff portion of the flight by pressing the compressor switch button until the adjacent indicator light is out This selection is designed to ensure safe operation through out the approved flight envelope actual performance will vary depending upon ambient conditions If runway conditions are short soft or grass and if pressure altitude temperature or humidity is high it is recommended ...

Page 469: ...ions by 40 fpm This selection is designed to ensure safe operation throughout the approved flight envelope actual perfor mance will vary depending upon ambient conditions If absolute maximum climb performance is desired the Climate Control System should be switched to the Air Conditioning Com pressor OFF mode by pressing the com pressor switch button until the adjacent indicator light goes out Iss...

Page 470: ...nditions by 40 fpm This selection is designed to ensure safe operation throughout the approved flight envelope actual perfor mance will vary depending upon ambient conditions If absolute maximum climb performance is desired the Climate Control System should be switched to the Air Conditioning Com pressor OFF mode by pressing the com pressor switch button until the adjacent indicator light goes out...

Page 471: ...ve one engine inoperative rate of climb at liftoff with the climate control system in operation and the Air Conditioning Compressor ON mode active increase the pressure altitude by 750 feet For example if the field pressure altitude is 1 000 feet use the maximum takeoff weight that corresponds to a pressure altitude of 1 750 feet TAKE OFF DISTANCE For takeoff with the climate control system in ope...

Page 472: ...keoff portion of the flight by pressing the compressor switch button until the adjacent indicator light is out CLIMB TWO ENGINE CLIMB BALKED LAND ING For climb performance with the climate control system in oper ation and the Air Conditioning Compressor ON mode active decrease the rate of climb as published in the POH AFM for the applicable conditions by 40 fpm If absolute maximum climb performanc...

Page 473: ...ference current weight and balance data in the POH AFM and compute proper airplane weight and bal ance information prior to each flight SECTION 7 SYSTEMS DESCRIPTIONS The A C Systems LLC Air Conditioning portion of the Auto matic Climate Control System operates on a closed vapor loop concept The heating portion operates in the same fashion as the non climate controlled airplane though it is contro...

Page 474: ...e air coming from the vents as well as the fan speed of the air con ditioning blower and air distribution change automatically Electric fan forced air directed through the condenser coil located in the empennage cools the hot high pressure R 134a refrigerant The condenser intake air is taken from two louvered panels on the left hand side of the airplane Con denser exhaust air exits through a louve...

Page 475: ...COLD AIR HEATED AIR FRESH AIR DEFOG OUTSIDE RAM AIR REAR FLOOR VENT REAR FLOOR VENT FRONT FLOOR VENT FRONT FLOOR VENT DEFOG VALVE REAR SEAT OVERHEAD VENTS EVAPORATOR AIR INTAKE EVAPORATOR BLOWER FRONT SEAT OVERHEAD VENTS CABIN AIR OUTLET VENT DISTRIBUTION PLENUM TH07C 143373AA AI Issued March 2017 ...

Page 476: ...ring cool cabin temperatures heated outside air will be delivered to the front and rear floor vents and the windshield based on temperature conditions and the mode of operation settings Additionally recirculated cabin air will be delivered to the ceil ing console vents at a low blower setting during the heating mode operation The blower speed of the air being delivered to the ceiling console vents...

Page 477: ... The Heating System performs the following functions 1 Warms cabin air temperature 2 Helps prevent fogging of windows 3 Provides for defog air Control of the heating system temperature cycle is done by controlling the mechanical thermostat which regulates the operation of the combustion heater located in the nose of the airplane The thermostat senses the heater duct temperature and cycles the comb...

Page 478: ... Master Heater Fan Switch should normally remain in the ON position at all times even when the airplane is shut down and the Master Battery and Alternator Switches are turned off Note that during flight operations when the landing gear is retracted heater operation and heater cooling is provided by ram air instead of the heater fresh air blower This applies to the heater 2 minute cool down period ...

Page 479: ...P N 58 590000 0091 FAA Approved MASTER HEATER FAN SWITCH TH07C 143372AA AI 17 of 24 Issued March 2017 ...

Page 480: ...n or Off manual control AUTO ALL SEASON STANDARD SETTING Air temperature air delivery and air distribution are regulated automatically to achieve and maintain the desired interior tem perature as quickly as possible The system automatically compensates for any variations in outside temperature In cold outside temperatures recirculated cabin air will be delivered to the ceiling console vents at a l...

Page 481: ...RE AND BUTTONS SIMULTANEOUSLY TURNS CLIMATE CONTROL SYSTEM ON RESUMES PRESENT MODE AND TEMPERATURE AUTOMATIC MODE ALL FUNCTIONS CONTROLLED AUTOMATICALLY ALL PREVIOUSLY SELECTED MANUAL SETTINGS ARE CANCELLED TURNS COMPRESSOR MODE ON OR OFF PRESS BUTTON TO TOGGLE COMPRESSOR SELECTION MODE ON AND OFF THE COMPRESSOR MODE IS ON WHEN THE ADJACENT ANNUNCIATOR LIGHT IS ILLUMINATED NOTE THAT THE LIGHT ONLY...

Page 482: ...or light adjacent to the compressor switch button is illuminated it indicates that the compressor mode is active and that the compressor is available for use if required by the climate control system This annunciator light does not indicate that the compressor is actually on only that the mode is active Pressing the compressor switch button alternately will toggle the compressor mode selection ON ...

Page 483: ...e digital dis play returns to the normal mode of interior temperature selec tion 5 seconds after either fan speed button is released The selected fan speed is maintained until it is changed or the AUTO button is depressed CABIN AIR CIRCULATION If cabin air circulation is desired the compressor mode can be selected OFF by pressing the compressor switch button until the adjacent annunciator light is...

Page 484: ...e of interior temperature selection The outside temperature display is not to be considered an indicator for possible icing conditions Ice formation can occur at indicated temperatures above freezing and in a multitude of conditions Refer to the POH AFM for information regarding flight into icing conditions NOTE The Climate Control System can display OAT This display is advisory only and may diffe...

Page 485: ...oors open for a few minutes prior to startup of the airplane to allow the hot air to escape When it is very hot and humid condensed water can drip from the evaporator drain tube onto the surface beneath the airplane for an extended period of time This is normal and does not indicate a leak or malfunction The condenser should be checked periodically for cleanli ness If clogged with dirt or debris t...

Page 486: ...pairs or maintenance to the air conditioning system require trained personnel and special tools If there should be any malfunction in the system contact the authorized Service Center SECTION 8 HANDLING SERV AND MAINT No Change Issued March 2017 ...

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Page 488: ... Baron Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for Airplanes with Kit 58 3400 0001 Garmin G1000 Airframe System Software Version 0508 13 REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 10 Original Issue Oct 2008 ...

Page 489: ... is to be attached to the Pilot s Operating Hand book and FAA Approved Airplane Flight Manual when the air plane is equipped with the Garmin G1000 Airframe System Software Version 0508 13 installed in accordance with Hawker Beechcraft Corporation Service Bulletin 34 3925 Kit 58 3400 0001 The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved ...

Page 490: ...FRAME SYSTEM SOFTWARE VERSION COCKPIT REFERENCE GUIDE P N 0508 13 190 00526 01 Revision B or Later SYSTEM ABBREVIATION SOFTWARE VERSION Primary Flight Display PFD1 8 10 Multifunction Display MFD1 8 10 Audio Control Panel Marker Beacon System GMA1 3 03 Attitude and Heading Reference System AHRS GRS1 2 11 Air Data Computer ADC GDC1 3 01 Integrated Avionics Unit GIA1 GIA2 5 42 Engine Airframe Unit L ...

Page 491: ...proach GPS Software Version 0508 13 1 CDI Key SELECTED GPS 2 Approach VERIFY ACTIVATED 3 NAV or APR Key PRESS GPS Displayed 4 Airspeed ESTABLISH Autopilot GSA PTCH CTL GSA PTCH MON GSA PTCH TRIM C GSA PTCH TRIM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW MON 2 13 Data Link GDL 69 3 20 00 Mode S Transponder GTX1 4 06 Airborne Weather Radar GWX 2 10 SYSTEM ABBREVIATION SOFTWARE VERSION Issued Oc...

Page 492: ...proach EXECUTE 6 CDI Key if required PRESS TO SELECT GPS 7 ALT Knob if required SET ALTITUDE At 400 feet minimum 8 AP Key PRESS TO ENGAGE AUTOPILOT 9 CWS PRESS TO CNX GA MODE ADJUST PITCH 10 HDG or NAV Key PRESS SECTION 5 PERFORMANCE No Change SECTION 6 WEIGHT AND BALANCE EQUIPMENT LIST No Change SECTION 7 SYSTEMS DESCRIPTION MONITORING THE ELECTRICAL SYSTEM The status of the electrical system can...

Page 493: ...ght AlternatorLoad High Caution amber ALT LOAD Left or Right Alternator load exceeds 100 amps Left Voltage Regulator Inoperative Caution amber LBUS VOLT HI Left bus voltage greater than 30 VDC Right Voltage Regulator Inoperative Caution amber RBUS VOLT HI Right bus voltage greater than 30 VDC Left Bus Voltage Low Caution amber LBUS VOLT LO Left bus voltage less than 24 VDC Suppressed below 500 RPM...

Page 494: ...l work with the Traffic Information Service TIS Where TIS is available the GTX 33 will display all responding ATCRBS Mode A and Mode C transponder equipped airplanes within seven nautical miles from 3000 feet below to 3500 feet above the airplane The TIS system only operates while in the ground based service area Transponder codes and mode selection are accessed by the XPDR softkey at the bottom o...

Page 495: ... psi WARNING Repeating Warning Alert OIL PRESS LO L or R oil press is less than 10 psi WARNING Repeating Caution Alert AFT DOOR Aft door not latched CAUTION Single Caution Alert ALT LOAD L or R alternator load exceeds 100 amps CAUTION Single Caution Alert FUEL QTY LO L or R fuel qty is less than or equal to 13 gal CAUTION Single Caution Alert L AIR PUMP Press Low Ops in icing conditions not approv...

Page 496: ...e re engaged after GO AROUND is selected SECTION 8 HANDLING SERVICING AND MAINTE NANCE No Change Caution Alert OIL PRESS LO L or R oil press is between 30 and 10 psi CAUTION Single Message AVIONICS FAN Cooling fan for remote avionics is inoperative ADVISORY None Advisory Alert BUSES TIED Left and Right Buses are tied ADVISORY None Message MFD FAN FAIL Cooling fan for the MFD is inoperative ADVISOR...

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Page 498: ... 2 FAA APPROVED Page 2 of 13 LOG OF REVISIONS FAA Approved Airplane Flight Manual Supplement G1000 Integrated Avionics on Hawker Beechcraft G58 REV NO PAGE NO S DESCRIPTION DATE OF REV 1 All Initial Release 6 4 10 2 All Add S W version 0857 09 See Cover ...

Page 499: ...CTION 1 GENERAL 4 SECTION 2 LIMITATIONS 7 SECTION 3 EMERGENCY PROCEDURES 12 SECTION 3A ABNORMAL PROCEDURES 12 SECTION 4 NORMAL PROCEDURES 12 SECTION 5 PERFORMANCE 12 SECTION 6 WEIGHT AND BALANCE EQUIPMENT LIST 12 SECTION 7 SYSTEMS DESCRIPTION 13 SECTION 8 HANDLING SERVICING AND MAINTENANCE 13 ...

Page 500: ... GA36 and GA37 antennas and GPS software version 3 2 or later approved version The G1000 GNSS navigation system in this aircraft is installed in accordance with AC 20 138A The Garmin G1000 Integrated Avionics GNSS navigation system as installed in this aircraft complies with the requirements of AC 20 138A and is approved for navigation using GPS and SBAS within the coverage of a Satellite Based Au...

Page 501: ...eans of Class II navigation in oceanic and remote navigation RNP 4 in accordance with AC 20 138A and FAA Order 8400 33 The G1000 can be used without reliance on other long range navigation systems Additional equipment may be required to obtain operational approval to utilize RNP 4 performance This does not constitute an operational approval The Garmin G1000 Integrated Avionics GNSS navigation syst...

Page 502: ... 01180 01 MODEL G58 BONANZA Rev 2 FAA APPROVED Page 6 of 13 Pilots and operators can view the LOA status at www Garmin com Aviation Databases Type 2 LOA Status Navigation information is referenced to WGS 84 reference system ...

Page 503: ...igation data is published for the procedure the database must not be used to conduct the procedure GPS SBAS based IFR enroute oceanic and terminal navigation is prohibited unless the pilot verifies and uses a valid compatible and current Navigation database or verifies each waypoint for accuracy by reference to current approved data Discrepancies that invalidate a procedure must be reported to Gar...

Page 504: ...on using the WFDE Prediction Program refer to GARMIN WAAS FDE Prediction Program part number 190 00643 01 WFDE Prediction Program Instructions For flight planning purposes operations within the U S National Airspace System on RNP and RNAV procedures when SBAS signals are not available the availability of GPS integrity RAIM shall be confirmed for the intended route of flight In the event of a predi...

Page 505: ...only one Long Range Navigation sensor Operator s mandatory crosschecking procedures must include referring to the MFD AUX GPS STATUS page to determine the state of GPS1 and GPS2 Whenever possible RNP and RNAV routes including Standard Instrument Departures SIDs and Obstacle Departure Procedures ODPs Standard Terminal Arrival STAR and enroute RNAV Q and RNAV T routes should be loaded into the fligh...

Page 506: ... VOR LOC GS navigation data is must be selected and presented on the CDI of the pilot flying Navigation information is referenced to WGS 84 reference system and should only be used where the Aeronautical Information Publication including electronic data and aeronautical charts conform to WGS 84 or equivalent Do not use SafeTaxi or Chartview functions as the basis for ground maneuvering SafeTaxi an...

Page 507: ...s alone for aircraft control without reference to the G1000 primary flight instruments or the aircraft standby instruments is prohibited Use of the Synthetic Vision system alone for navigation or obstacle or terrain avoidance is prohibited Use of the Synthetic Vision system traffic display alone to avoid other aircraft is prohibited ...

Page 508: ...splay backup mode is required Select display backup mode on the G1000 system NOTE When display backup mode is selected the MFD will initially present a non SVS blue sky over solid brown ground display SVS will be presented on the backup display within 20 seconds if it was enabled on the PFD when display backup was selected SECTION 4 NORMAL PROCEDURES For normal operating procedures refer to the ap...

Page 509: ...A APPROVED Page 13 of 13 SECTION 7 SYSTEMS DESCRIPTION For systems descriptions refer to the Baron G58 AFM 58 590000 67 or the Garmin G1000 Pilots Guide for the Beechcraft G58 190 00629 03 Rev A or later SECTION 8 HANDLING SERVICING AND MAINTENANCE No Change ...

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Page 511: ...MIN hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unautho...

Page 512: ...24 GARMIN International Inc Log of Revisions FAA Approved AIRPLANE FLIGHT MANUAL SUPPLEMENT G1000 NXi Integrated Avionics System and GFC 700 AFCS for Textron Aviation G36 Bonanza and G58 Baron Aircraft REV NO PAGE NO S DESCRIPTION DATE OF APPROVAL FAA APPROVED 1 ALL Original Issue See Cover See Cover ...

Page 513: ...Textron Aviation G36 Bonanza and G58 Baron with G1000 NXi 190 02128 03 Rev 1 Page 4 of 24 FAA APPROVED This page intentionally left blank ...

Page 514: ...1000 NXi FAA APPROVED Page 5 of 24 Table of Contents GENERAL 7 LIMITATIONS 13 EMERGENCY PROCEDURES 15 ABNORMAL PROCEDURES 18 NORMAL PROCEDURES 22 PERFORMANCE 22 WEIGHT AND BALANCE EQUIPMENT LIST 22 AIRPLANE AND SYSTEMS DESCRIPTIONS 23 HANDLING SERVICE AND MAINTENANCE 23 ...

Page 515: ...Textron Aviation G36 Bonanza and G58 Baron with G1000 NXi 190 02128 03 Rev 1 Page 6 of 24 FAA APPROVED This page intentionally left blank ...

Page 516: ...are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane The GARMIN G1000 NXi system installed in this aircraft provides a fully integrated Display Communications Navigation and Flight Control System Functions provided by the G1000 NXi system include Primary Flight Information Powerplant Monitoring Navigation Communic...

Page 517: ...CAUTIONS and NOTES found throughout the AFMS WARNING OPERATING PROCEDURES TECHNIQUES ETC WHICH COULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED CAUTION OPERATING PROCEDURES TECHNIQUES ETC WHICH COULD RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED NOTE Operating procedures techniques etc which is considered essential to emphasize ...

Page 518: ...st AFCS Automatic Flight Control System AFM Airplane Flight Manual AFMS Airplane Flight Manual Supplement AHRS Attitude and Heading Reference System ALT Altitude or AFCS altitude hold mode or ALT button on the GDU AMMD Airport Moving Map Display AP Autopilot ATC Air Traffic Control AUX Auxiliary BARO Barometric Setting BC Back Course CDI Course Deviation Indicator COM Communication radio CRG Cockp...

Page 519: ...ntrol GNSS Global Navigation Satellite System GP GPS Glide Path GPS Global Positioning System GPWS Ground Proximity Warning System GS Glide Slope HDG AFCS heading mode or the HDG button on the GDU HSI Horizontal Situation Indicator IFR Instrument Flight Rules ILS Instrument Landing System INH Inhibit LNAV Lateral Navigation LNAV V Lateral Navigation with Advisory Vertical Guidance LNAV VNAV Latera...

Page 520: ...tion OPT Option PDA Premature Descent Alert PFD Primary Flight Display PFT Pre Flight Test PIT AFCS Pitch Mode POH Pilot s Operating Handbook PROC Procedure Button on the GDU PTCH Pitch ROL AFCS roll mode SBAS Satellite Based Augmentation System STC Supplemental Type Certificate SVT Synthetic Vision Technology TAWS Terrain Awareness and Warning System TWY Taxiway VAPP AFCS VOR Approach Mode VFR Vi...

Page 521: ...on with G1000 NXi 190 02128 03 Rev 1 Page 12 of 24 FAA APPROVED VPTH Vertical Path VS Vertical Speed WAAS Wide Area Augmentation System WFDE WAAS Fault Detection Exclusion WGS 84 World Geodetic System 1984 XM LTNG XM Satellite System Lighting ...

Page 522: ...cument G36 Bonanza 190 02180 00 Garmin G1000 NXi Cockpit Reference Guide A36 G36 Series G58 Baron 190 02182 00 Garmin G1000 NXi Cockpit Reference Guide Beechcraft 58 G58 Series G1000 NXI LIMITATIONS GROUND MANEUVERING Do not use SafeTaxi FliteCharts ChartView or SurfaceWatch functions as the basis for ground maneuvering These functions do not comply with the requirements of AC 20 159 and are not q...

Page 523: ...nderstorm penetration is prohibited Datalink weather information displayed by the G1000 NXi system is limited to supplemental use only XM or FIS B weather data is not a source of official weather information and is intended only as an aid to enhance situational awareness of hazardous weather FMS FLIGHT PLAN Do not delete the arrival airport or runway waypoint within a loaded arrival procedure Arri...

Page 524: ... and Aural Taxiway Message 1 Takeoff ABORT 2 Throttle Control IDLE 3 Brakes APPLY 4 Aircraft Position and Runway Assignment CONFIRM If Aircraft Position and Runway Assignment are Correct 5 SurfaceWatch Alerts OFF From the MFD AUX System Setup page Set SurfaceWatch Alerts OFF NOTE SurfaceWatch Alerts should be turned ON as soon as practical after takeoff to restore functionality for remainder of fl...

Page 525: ...ts OFF From the MFD AUX System Setup page Set SurfaceWatch Alerts OFF NOTE SurfaceWatch Alerts should be turned ON as soon as practical after landing to restore functionality for ground operations RUNWAY TOO SHORT DURING TAKEOFF Red Annunciator Is Displayed and Aural Runway Too Short Message 1 Takeoff ABORT 2 Throttle Control IDLE 3 Brakes APPLY 4 Aircraft Position and Runway Assignment Confirm 5 ...

Page 526: ...SHORT DURING LANDING Red Annunciator Is Displayed and Aural Runway Too Short Message 1 BALKED LANDING Procedure EXECUTE 2 Aircraft Position and Runway Assignment CONFIRM 3 Ensure correct destination runway and required landing distance have been entered into the G1000 NXi system From the FPL SurfaceWatch Setup page ...

Page 527: ... off from a runway different than that entered in the FPL SurfaceWatch Setup Page on the MFD 1 Aircraft Position Runway Assignment CONFIRM If Aircraft Position and Runway Assignment are Correct 2 Takeoff CONTINUE AS DESIRED If Aircraft Position and Runway Assignment are Not Correct or Cannot be Determined 3 Takeoff ABORT 4 Throttle Control IDLE pull full out 5 Brakes APPLY 6 Enter correct origin r...

Page 528: ...ferent than that entered on the MFD FPL SurfaceWatch Setup Page 1 Aircraft Position Runway Assignment CONFIRM If Aircraft Position and Runway Assignment are Correct 2 Approach and Landing CONTINUE AS DESIRED If Aircraft Position and Runway Assignment are Not Correct or Cannot be Determined 3 BALKED LANDING Procedure EXECUTE 4 Enter correct destination runway and required landing distance into the ...

Page 529: ...ng procedures to inhibit the SurfaceWatch system 1 MFD AUX System Setup Page VIEW 2 SurfaceWatch Alerts SELECT 3 SurfaceWatch Alerts SELECT OFF NOTE After inhibiting SurfaceWatch the following will post as an alert on the PFD in the Alerts window SURFACEWATCH INHIBITED SurfaceWatch Inhibited SurfaceWatch Alerts will remain inhibited until manually un inhibited by the pilot or a power cycle of the ...

Page 530: ...H RUNWAY POSITION DATA There are certain runways at various worldwide airports that do not have valid position data for the SurfaceWatch system to use If such a runway is entered into the system for either takeoff or landing via the FPL SurfaceWatch Setup Page on the MFD the following will post as a message on the PFD in the alerts window NO RUNWAY POSITION DATA Inhibit SurfaceWatch No runway posi...

Page 531: ...ED c White PFT Message ILLUMINATED 5 seconds d White PFT Message EXTINGUISHED e Autopilot Disconnect Tone SOUNDS NOTE If the autopilot disconnect tone is not heard after the white PFT message extinguishes verify the aural alert can be heard after reengaging and disconnecting the autopilot f Autopilot ENGAGE g AP DISC TRIM INTER Button PRESS h Autopilot Disconnect Tone SOUNDS PERFORMANCE No Change ...

Page 532: ...nd G58 Baron with G1000 NXi FAA APPROVED Page 23 of 24 AIRPLANE AND SYSTEMS DESCRIPTIONS STANDARD AVIONICS HANDLING SERVICE AND MAINTENANCE No Change Refer to Pilot s Operating Handbook and FAA Approved Airplane Flight Manual or appropriate supplement ...

Page 533: ...ndow in the lower right corner of the PFD If the G1000 NXi system is unable to transmit ADS B OUT messages the following message will post on the PFD in the alerts window XPDR1 ADS B NO POS Transponder ADS B is not transmitting position If the above message is received verify valid GPS position is available 1 MFD AUX GPS Status Page VERIFY GPS Position PRESSURE ALTITUDE BROADCAST INHIBIT While con...

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Page 536: ... PERMISSION OF MILLENNIUM CONCEPTS INC ADDITIONALLY USE OF THE INFORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY MILLENNIUM CONCEPTS INC TABLE OF CONTENTS LIST OF EFFECTIVE PAGES 2 LOG OF REVISIONS 2 TABLE OF CONTENTS 3 INTRODUCTION 4 SECTION 1 GENERAL 5 SECTION 2 LIMITATIONS 5 SECTION 3 EMERGENCY PROCEDURES 11 SECTION 3A ABNORMAL PROCEDURES 11 SECTION 4 NORMAL PROCEDURES 11 SECTION 5 ...

Page 537: ...MATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY MILLENNIUM CONCEPTS INC INTRODUCTION This supplement must be attached to the FAA Approved Airplane Flight Manual when the Millennium Interior Upgrade has been installed in the airplane The information in this document supplements or supersedes the basic manual only in those areas listed For limitations procedures performance and loading info...

Page 538: ... the most upright position for takeoffs and landings Occupied aft facing seats must have the headrests extended to fully support the occupant s head PLACARDS MARKINGS Placards markings are required to remind the flight crew and occupants of operating limitations and safety device limitations The following illustrations depict placards markings pertinent to operations and safety of flight The placa...

Page 539: ...ANEUVERS INCLUDING SPINS APPROVED AIRSPEED LIMITATIONS IAS MAX LDG GEAR EXTENDED NORMAL 152 KTS MAX FLAPS EXTENDED 15 DOWN 152 KTS MAX FLAPS EXTENDED NORMAL 122 KTS MAX DESIGN MANEUVER SPEED 156 KTS MIN CONTROL SPEED SINGLE ENGINE 84 KTS NEVER EXCEED SPEED 223 KTS MAX STRUCTURAL CRUISE SPEED 195 KTS OPERATIONAL LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE ...

Page 540: ...C94CE02CI958 Adjacent to Openable Cabin Window Handles Placard part number 2033 1100351 061 Emergency Exit Mechanism Operation is installed in lieu of factory placard part number C94CE02CI978 The content of the placard is unchanged On Face of Emergency Exit Latch Cover Placard part number 2033 1100351 063 Emergency Exit is installed in lieu of factory placard part number C94CE02CI954 The content o...

Page 541: ...lity Door Removal Kit Installed in lieu of factory placard number C95TH02C0161 In addition the following placards are required On Table Surround if Table is Installed 2033 1100351 007 Table Lid Closure On Underside of Table Leaf Visible When Table is Folded If Table is Installed 2033 1100351 039 Table Leaf Stowage On LH Window Panel near Footman Loops 2033 1100351 069 Cargo Retention WHEN UTILITY ...

Page 542: ...ORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY MILLENNIUM CONCEPTS INC On Lower Bulkhead Above Return Air Vent 2033 1100351 071 Return Air Duct On LH Window Panel in Cockpit and RH Cabin Window Panel Adjacent to Row 2 Seat 2033 1100351 073 Armrest Position On Vertical Face of Quadrant Cover 2033 1100351 043 Cowl Flaps On Forward Cargo Door Above Stowage Pocket 2033 1100351 047 XXX Main...

Page 543: ... EXPRESS WRITTEN PERMISSION OF MILLENNIUM CONCEPTS INC ADDITIONALLY USE OF THE INFORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY MILLENNIUM CONCEPTS INC On Aft Face of Cup Holder Located in the Cockpit Quadrant Cover Drawer 2033 1100351 077 Quadrant Cover Drawer Latch On Quadrant Cover Pull Out Drawer Between Cup Holders 2033 1100351 081 Power Quadrant Cupholder On Armrest At Forward E...

Page 544: ...NNIUM CONCEPTS INC SECTION 3 EMERGENCY PROCEDURES NO CHANGE SECTION 3A ABNORMAL PROCEDURES NO CHANGE SECTION 4 NORMAL PROCEDURES The following checks must be added to the normal procedures in the basic Model G58 FAA Approved Airplane Flight Manual BEFORE ENGINE STARTING 1 Seats POSITION FOR TAKE OFF a Seat Backs UPRIGHT b Rear Facing Seat Headrests RAISE c Seat Center Armrests DOWN d Cabin Table I...

Page 545: ...in an accident and serious or fatal injury On PAYLOAD LOCATIONS diagram revise flag note 4 and add flag note 5 as follows Maximum Baggage Weight is 120 pounds includes coat hanger bar weight Maximum Coat Hanger Bar weight is 10 pounds EQUIPMENT LIST The following equipment must be listed to the aircraft serial number specific equipment list For interiors with the club seat arrangement Equipment De...

Page 546: ...as shown The pedestal is located below the center portion of the instrument subpanel The upper portion of the pedestal houses the throttle black propeller blue and mixture red control levers The elevator trim tab control is located on the left side of the pedestal The rudder and aileron trim tab controls are mounted on the front of the pedestal along with the cowl flap control Underneath the trim ...

Page 547: ...Lift the lever up and then allow the seat backrest to recline to the desired position To bring the backrest upright pull the backrest to the upright position as desired The mechanism will automatically lock as it is pulled upright To fold over the seat backrest use the red lever located at the bottom inboard side of the seat backrest Lift the lever up and rotate the backrest towards the seat botto...

Page 548: ... and right side of the pedestal in the pilot and co pilot foot wells In the case of the club arrangement with the side table there are additional accent lights in the bottom of the cup holders located forward and aft of the side table The accent lights are designed to be on when the aircraft is powered on Add the following section as shown CABIN SIDE TABLE The club arrangement provides a cabin sid...

Page 549: ...601 Rev IR Bonanza Models A36 G36 A36TC B36TC F33A F33C Baron Models 58 58A G58 B55 E55 Pilot s Operating Handbook Supplement For STC SA02387AK Exterior LED Lighting Suite Airplane Serial number _______________________________ Airplane Registration Number _________________________ Page 1 of 4 ...

Page 550: ...es a Taxi Light attached to the nose landing gear strut Ground Awareness Beacon Lighting on the vertical stabilizer and combined Navigation Forward Tail Anti Collision Strobe lighting on each wing tip A Step Light is installed on the right side fuselage A Wing Ice Inspection Light is installed on the left engine nacelle Bonanza Baron LED Anti Collision Lighting Update The FAA certified LED Anti Co...

Page 551: ...g Update The LED Forward Navigation Lighting is located on the end of each wingtip and is controlled by the NAV switch The LED Tail Navigation lighting is located on the end of each wingtip and is controlled by the NAV switch The Tail Navigation Light in the tail cone is no longer present and the opening is closed with a patch Page 3 of 4 ...

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Page 569: ...contained herein supplements or supersedes the basic Flight Manual only in those areas listed when the aircraft is modified in accordance with STC number SA03065CH D for installation of the AlC Systems LLC Air Conditioning System The information contained in this document supplements or supersedes the basic Airplane Flight Manual only in those areas listed herein For Limitations Procedures and Per...

Page 570: ...58 E55A E55 D55A AND D55 Page 2 FAA Approved 04 23 2012 A C SYSTEMS LLC DICKSON TN REVISION LOG REV PAGES DESCRIPTION REVISED DATE NO AFFECTED OF REVISIONS BY IR ALL Initial Release of AFMS 04 23 2012 The revised portions of the affected pages are indicated by vertical black lines in the right margin ...

Page 571: ...e Automatic Climate Control should be selected Climate Control System OFF ELECTRICAL SMOKE OR FIRE OFF on the Automatic Climate Control should be selected Climate Control System OFF RIGHT ENGINE FAILURE After securing and feathering the right engine The Air Conditioning Compressor OFF mode on the Automatic Climate Control should be selected by pressing the button until the adjacent indicator light...

Page 572: ...g Compressor ON mode in operation increase the Ground Roll distance as published in the POH for the applicable conditions by 4 and the corresponding Total Distance over a 50ft obstacle by 5 If this incremental distance is not available select the Compressor OFF mode during the takeoff portion of the flight by pressing the button until the adjacent indicator light is out This selection is designed ...

Page 573: ... the Climate Control System should be switched to the Air Conditioning Compressor OFF mode by pressing the button until the adjacent indicator light goes out NORMAL LANDING No change to this procedure SHORT FIELD LANDING No change to this procedure BALKED LANDING No change to this procedure NOTE For climb performance with the Air Conditioning Compressor ON mode in operation decrease the rate of cl...

Page 574: ... adjacent indicator light is out ACCELERATE GO DISTANCE For takeoff with the climate control system in operation and the Air Conditioning Compressor ON mode active increase the Accelerate Go Distance as published in the POH for the applicable conditions by increasing the pressure altitude by 750 feet For example if the field pressure altitude is 1 000 feet use the Accelerate Go Distance that corre...

Page 575: ...to regulate the evaporator coil temperature and to prevent the coil from freezing up During operation during warm cabin temperatures the Automatic Climate Control System operates in the air conditioning mode supplying cooled dehumidified air to the ceiling console vents and the flood ducts above the rear seats When the system switches to heating operation during cool cabin temperatures heated outs...

Page 576: ...upplement Document No FTA 010 6 Beechcraft Baron Models Revision IR G58 58A 58 E55A E55 D55A AND D55 Page 8 FAA Approved 04 23 2012 SECTION 7 SYSTEMS DESCRIPTION continued Figure 1 ENVIRONMENTAL CONTROL SYSTEM AIRFLOW DIAGRAM ...

Page 577: ...ion or due to the shut down of the aircraft after a flight a heater timer module and a heater control module will operate the heater fresh air blower automatically for approximately 2 minutes to cool the combustion heater This 2 minute cool down function operates even with the aircraft battery and alternator master switches turned off The 2 minute cool down function can be interrupted by turning t...

Page 578: ...essing this button toggles the compressor selection On and Off Raises cabin temperature in 1 increments The temperature display can be switched from C to F and vice versa as follows Press and hold the temperature and buttons simultaneously Displays outside air temperature for 5 seconds Raises fan speed Possible in all Mode selections Speed is indicated as a percentage in the display for 5 seconds ...

Page 579: ...e button indicates when this mode is active Press the button again to cancel the defog mode Air Conditioning Compressor Mode on off When maximum aircraft performance is desired the air conditioning compressor mode can be switched off In this case the system no longer provides full climate control If the cabin becomes too warm press the switch again to turn the he air conditioning compressor mode O...

Page 580: ...onditions NOTE The Climate Control System can display OAT This display is advisory only and may differ from other OAT indications displayed in the cockpit OFF When the OFF button is depressed the entire climate control system is switched off In this mode of operation the heater ECS mixing valve closes the hot air supply from the engine heat exchanger This mode does NOT need to be selected prior to...

Page 581: ...evision IR G58 58A 58 E55A E55 D55A AND D55 Page 13 FAA Approved 04 23 2012 SECTION 8 HANDLING SERVICE MAINTENANCE No change to this section SECTION 9 SUPPLEMENTS Add A C Systems LLC Air Conditioning System Aircraft Flight Manual Supplement to SECTION 9 when the system is installed ...

Page 582: ...ed NOTE Supplements are provided in a supplement pack that includes all supplements for a particular flight manual All applicable supplements must be inserted in the manual Supplements not applicable to an airplane due to airworthiness authority certification requirements or equipment configuration may be omitted from the manual Flight Manual Supplement Packs are available on the web at http pubs ...

Page 583: ...ance This Supplement is Applicable to the Following Manual s 58 590000 67 Airplane Serial Number _________________________ Airplane Registration Number ____________________ Copyright 2014 Beechcraft Corporation All rights reserved Hawker and Beechcraft are trademarks of Beechcraft Corporation Issued December 2014 P N 58 590000 0089 1 of 12 ...

Page 584: ...REVISIONS Model G58 Baron TH 2125 and After Pilot s Operating Handbook and Manufacturer Approved Airplane Flight Manual Supplement for Low Speed Endurance REV NO PAGE NO S DESCRIPTION DATE OF REV 0 1 thru 12 Original Issue December 2014 ...

Page 585: ...ECTION 8 HANDLING SERV AND MAINT Page 11 SECTION 1 GENERAL The information in this supplement is Manufacturer approved material and must be attached to the Pilot s Operating Hand book and FAA Approved Airplane Flight Manual when the air plane is operated during low speed endurance in accordance with Beechcraft Corporation approved data SECTION 2 LIMITATIONS No change SECTION 3 EMERGENCY PROCEDURES...

Page 586: ...performance data is calculated over a range of power settings from 16 to 25 in Hg All performance data provided in this supplement is calculated using a propeller setting of 2300 RPM and a fuel mixture set ting of 20 C lean of peak EGT NOTE Reserve fuel calculation provided in this supplement assumes 45 minutes at 2300 RPM and a power setting of 16 in Hg Issued December 2014 ...

Page 587: ...P N 58 590000 0089 5 of 12 Issued December 2014 58 590000 0089_text_foldout fm Page 1 Friday December 12 2014 8 22 AM ...

Page 588: ...143 10 000 3 27 16 46 7 7 129 150 12 000 7 19 16 48 8 0 130 156 14 000 10 14 16 49 8 2 130 161 16 000 14 7 16 51 8 5 131 167 SL 36 97 16 35 5 9 103 107 2 000 32 90 16 37 6 2 110 118 4 000 29 84 16 39 6 5 115 127 6 000 25 77 16 41 6 8 119 135 8 000 21 70 16 43 7 1 121 142 10 000 17 63 16 45 7 4 123 148 12 000 13 55 16 46 7 7 124 154 14 000 10 50 16 48 8 0 124 160 16 000 6 43 16 49 8 2 124 165 T HA ...

Page 589: ...7 of 12 P N 58 590000 0089 Issued December 2014 ...

Page 590: ...P N 58 590000 0089 8 of 12 Issued December 2014 58 590000 0089_text_foldout fm Page 2 Friday December 12 2014 8 22 AM ...

Page 591: ...P N 58 590000 0089 Issued December 2014 9 of 12 58 590000 0089_text_foldout fm Page 3 Friday December 12 2014 8 22 AM ...

Page 592: ...10 of 12 P N 58 590000 0089 Issued December 2014 ...

Page 593: ...11 of 12 P N 58 590000 0089 SECTION 6 WEIGHT AND BALANCE EQUIP MENT LIST No change SECTION 7 SYSTEMS DESCRIPTION No change SECTION 8 HANDLING SERVICING AND MAINTENANCE No change Issued December 2014 ...

Page 594: ...12 of 12 P N 58 590000 0089 THIS PAGE INTENTIONALLY LEFT BLANK Issued December 2014 ...

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Page 659: ...0857 06 Software Description Compatible LRU P N s System Status Page Name P N VER GTX 33 Mode S Transponder 011 00779 10 GTX1 006 B0172 XX 4 06 GEA 71 No 1 Engine Airframe Adapter Left 011 00831 00 GEA1 006 B0193 05 2 07 GEA 71 No 2 Engine Airframe Adapter Right 011 00831 00 GEA2 006 B0193 05 2 07 GDC1 006 B0261 11 3 01 GDC 74A ADC 011 00882 00 or 011 00882 10 GDC1 FPGA 006 C0055 00 01 05 GMU1 006...

Page 660: ...9 00 02 00 GRS 77 AHRS 011 00868 10 GRS1 MV DB 3 006 D0159 01 2005 00 GMA 1347 Audio Panel 011 00809 00 GMA1 006 B0203 42 4 02 GDL 69A Data Link 011 00987 00 GDL69 006 B0317 14 3 20 00 2 006 B0398 20 2 13 GSA 81 Autopilot Servo Qty 4 011 00878 00 1 006 D0373 02 2 02 GWX 006 B0266 09 2 10 GWX 68 Weather Radar 011 00883 20 GWX FPGA 006 C0042 06 3 01 1 All LRU entries that begin with GFC CERT 2 All L...

Page 661: ...0857 05 Software Description Compatible LRU P N s System Status Page Name P N VER GTX 33 Mode S Transponder 011 00779 10 GTX1 006 B0172 XX 4 06 GEA 71 No 1 Engine Airframe Adapter Left 011 00831 00 GEA1 006 B0193 05 2 07 GEA 71 No 2 Engine Airframe Adapter Right 011 00831 00 GEA2 006 B0193 05 2 07 GDC1 006 B0261 11 3 01 GDC 74A ADC 011 00882 00 or 011 00882 10 GDC1 FPGA 006 C0055 00 01 05 GMU1 006...

Page 662: ...9 00 02 00 GRS 77 AHRS 011 00868 10 GRS1 MV DB 3 006 D0159 01 2005 00 GMA 1347 Audio Panel 011 00809 00 GMA1 006 B0203 33 3 03 GDL 69A Data Link 011 00987 00 GDL69 006 B0317 14 3 20 00 2 006 B0398 20 2 13 GSA 81 Autopilot Servo Qty 4 011 00878 00 1 006 D0373 02 2 02 GWX 006 B0266 09 2 10 GWX 68 Weather Radar 011 00883 20 GWX FPGA 006 C0042 06 3 01 1 All LRU entries that begin with GFC CERT 2 All L...

Page 663: ...s G1000 Airframe System Software Version 0508 13 Software Description Compatible LRU P N s System Status Page Name P N VER GTX 33 Mode S Transponder 011 00779 10 GTX1 006 B0172 XX 4 06 GEA 71 No 1 Engine Airframe Adapter Left 011 00831 00 GEA1 006 B0193 05 2 07 GEA 71 No 2 Engine Airframe Adapter Right 011 00831 00 GEA2 006 B0193 05 2 07 GDC1 006 B0261 11 3 01 GDC 74A ADC 011 00882 00 or 011 00882...

Page 664: ...B0223 09 2 11 GRS1 FPGA 006 C0049 00 02 00 GRS 77 AHRS 011 00868 10 GRS1 MV DB 3 006 D0159 01 2005 00 GMA 1347 Audio Panel 011 00809 00 GMA1 006 B0203 33 3 03 GDL 69A Data Link 011 00987 00 GDL69 006 B0317 14 3 20 00 2 006 B0398 20 2 13 GSA 81 Autopilot Servo Qty 4 011 00878 00 1 006 D0373 02 2 02 GWX 006 B0266 09 2 10 GWX 68 Weather Radar 011 00883 20 GWX FPGA 006 C0042 06 3 01 1 All LRU entries ...

Page 665: ...GTX1 GIA1 GTX 33 Mode S Transponder 011 00779 10 GTX1 GIA2 006 B0172 XX 4 02 GEA1 GIA1 GEA 71 Engine Airframe Unit Left 011 00831 00 GEA1 GIA2 006 B0193 04 2 06 GEA2 GIA1 GEA 71 Engine Airframe Unit Right 011 00831 00 GEA2 GIA2 006 B0193 04 2 06 GDC1 GIA1 006 B0261 03 2 05 GDC 74A ADC 011 00882 00 GDC1 FPGA 006 C0055 00 01 05 GMU1 006 B0224 00 2 01 GMU 44 Magnetometer 011 00870 00 GMU1 FPGA 006 C0...

Page 666: ...A1 GMA 1347 Audio Panel 011 00809 00 GMA1 GIA2 006 B0203 06 2 07 GDL 69A Data Link 011 00987 00 GDL69 006 B0317 10 3 00 00 3 006 B0398 15 2 08 GSA 81 Autopilot Servo Qty 4 011 00878 00 2 006 D0373 01 2 01 GWX 006 B0266 07 2 01 GWX 68 011 00883 20 GWX FPGA 006 C0042 05 3 00 1 Garmin Service Bulletin 0418 must be complied with 2 All LRU entries that begin with GFC1 CERT or GFC2 CERT 3 All LRU entrie...

Page 667: ...GTX1 GIA1 GTX 33 Mode S Transponder 011 00779 10 GTX1 GIA2 006 B0172 XX 4 02 GEA1 GIA1 GEA 71 Engine Airframe Unit Left 011 00831 00 GEA1 GIA2 006 B0193 04 2 06 GEA2 GIA1 GEA 71 Engine Airframe Unit Right 011 00831 00 GEA2 GIA2 006 B0193 04 2 06 GDC1 GIA1 006 B0261 03 2 05 GDC 74A ADC 011 00882 00 GDC1 FPGA 006 C0055 00 01 05 GMU1 006 B0224 00 2 01 GMU 44 Magnetometer 011 00870 00 GMU1 FPGA 006 C0...

Page 668: ... GDL 69A Data Link 011 00987 00 GDL69 006 B0317 10 3 00 00 3 006 B0398 12 2 05 GSA 81 Autopilot Servo Qty 4 011 00878 00 2 006 D0373 00 2 00 GWX 006 B0266 07 2 01 GWX 68 011 00883 20 GWX FPGA 006 C0042 05 3 00 1 Garmin Service Bulletin 0418 must be complied with 2 All LRU entries that begin with GFC1 CERT or CFC2 CERT 3 All LRU entries that begin with GSA 4 GRS1 MV DB Must be updated by Garmin Man...

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