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Beechcraft C23 SUNDOWNER 180, Pilot Operating Handbook

The Beechcraft C23 Sundowner 180 is a reliable aircraft equipped with exceptional features for pilots. To ensure smooth operations and optimal performance, we provide a comprehensive and free Pilot Operating Handbook (POH) for download on our website. Access the manual at manualshive.com to unlock valuable insights and guidelines for safer flights.

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Summary of Contents for C23 SUNDOWNER 180

Page 1: ...T WITHIN REACH OF THE PILOT DURING ALL FLIGHT OPERATIONS THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 Mfr s Serial No Registration No FAA Approved by THIS HANDBOOK SUPERSEDES ALL BEECH PUBLISHED OWNERS MANUALS AND CHECK LISTS ISSUED FOR THIS AIRPLANE WITH THE EXCEPTION OF FAA APPROVED AIRPLANE FLIGHT MANUALS P N 169 590008 23 P N 169 590008 23A4 Issued F...

Page 2: ...PUBLISHED BY COMMERCIAL PUBLICATIONS BEECH AIRCRAFT CORPORATION WICHITA KANSAS 67201 U S A Geechcraft General Avtation A RilyNieert Company Manufacturers Associalion ...

Page 3: ...same place in all of the handbooks In recent years BEECHCRAFT handbooks contained most of the data now provided however the new handbooks contain more detailed data and some entirely new data For example attention is called to Section X SAFETY IN FORMATION While little of the information is new and every pilot has been exposed to the basic fundamentals BEECHCRAFT feels it is highly important to ha...

Page 4: ...ECTION 1 General SECTION 2 Limitations SECTION 3 Emergency Procedures SECTION 4 Normal Procedures SECTION 5 Performance SECTION 6 Weight and Balance Equipment List SECTION 7 Systems Description SECTION 8 Handling Servicing and Maintenance SECTION 9 Supplements SECTION 10 Safety Information b February 1979 ...

Page 5: ...e Performance chart 5 19 Shifted Material and Added Notes 5 20 Shifted Material 5 21 Added New Page and Shifted Material 5 22 Added New Page 7 1 Revised Table of Contents 7 3 Revised Table of Contents 7 5 Shifted Material 7 6 Shifted Material 7 11 Shifted Material and Revised Flight Instruments 7 25 Shifted Material and Revised Alternator 7 26 and Shifted Material and Revised 7 27 External Power R...

Page 6: ...LOG OF REVISIONS Page Description 7 32 Shifted Material 8 1 Revised Table of Contents 8 10 and Shifted Material and Revised 8 11 External Power Receptacle 2 of 2 Page A ...

Page 7: ...ial 3 1 Revised Table of Contents 3 3 Revised Emergency Airspeeds and Added Note 3 7 Revised Emergency Descent 3 8 and 3 9 Added Starter Engaged Warning Light Illuminated and Revised Alternator Out Procedure 3 10 and 3 11 Shifted Material 4 1 Revised Table of Contents 4 5 Shifted Material 4 6 Revised Before Starting 4 7 Shifted Material 4 8 Revised Starting 4 9 Revised Before Take off 4 10 thru 4 ...

Page 8: ... Description 7 20 Revised Starter 7 21 and 7 23 Revised Fuel System 8 15 Revised Tires 8 34 and 8 35 Revised Consumable Materials 8 41 Revised Power Plant 10 1 Thru 10 67 BevisedSafety Section Dated March 1981 2 of 2 Page A ...

Page 9: ... A2 New 2 1 Update Table of Contents 2 5 Add Fuel Additives 2 6 Shift Material 2 7 Revise Weight Limits and Center of Gravity Limits 2 8 Revise Maneuver Limits 4 1 Update Table of Contents 4 8 Revise After Starting and Before Taxi 4 10 Shift Material 4 11 Revise Descent 4 15 Add Noise Characteristics 8 8 Revise Jacking 8 35 Revise Consumable Materials Page A ...

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Page 11: ...tch designation 4 7 Add 28 volt system information 4 8 4 9 Shift material 4 12 Revise switch designation 7 2 7 3 Update Table of Contents 7 11 Revise Switches 7 24 7 25 Revise switch designation Revise Battery 7 25 Revise Alternator 7 26 7 27 Shift material and add revised External Power Receptacle 7 32 Revise switch designation 8 2 Update Table of Contents 8 11 Revise External Power 8 14 8 15 Rev...

Page 12: ......

Page 13: ...79 PAGES DESCRIPTION Title Page Original A Page Original a and b Original 1 1 thru 1 18 Original 2 1 thru 2 32 Original 3 1 thru 3 12 Original 4 1 thru 4 14 Original 5 1 thru 5 20 Original 6 1 thru 6 20 Original 7 1 thru 7 32 Original 8 1 thru 8 46 Original Section 9 See Log of Supplements 10 1 thru 10 30 Original A Page A ...

Page 14: ......

Page 15: ...GE Thank You 1 3 Important Notice 1 3 Use of the Handbook 1 4 Revising the Handbook 1 5 Supplernents Revision Record 1 6 Vendor Issued STC Supplements 1 6 Airplane Three View 1 7 Ground Turning Clearance 1 8 Descriptive Data Engine 1 9 Propeller 1 9 Fuel 1 9 Oil Capacity 1 10 February 1979 1 1 ...

Page 16: ...m Certificated Weights 1 11 Cabin and Entry Dimensions 1 11 Baggage Space and Entry Dimensions 1 11 Specific Loadings 1 11 Symbols Abreviations and Terminology General Airspeed 1 12 Meteorological 1 14 Power 1 15 Engine Controls and Instruments 1 15 Airplane Performance and Flight Planning 1 16 Weight and Balance 1 16 1 2 February 1979 ...

Page 17: ... in accordance with the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual ancVor placards which are located in the airplane As a further reminder the owner and operator of this airplane should also be familiar with the Federal Aviation Regulations applicable to the operation and maintenance of the airplane and FAR Part 91 General Operating and Flight Rules Further the airplane mus...

Page 18: ...ssary documents may be maintained for the safe and efficient operation of the airplane The handbook has been prepared in loose leaf form for ease in maintenance and in a convenient size for storage The handbook has been arranged with quick reference tabs imprinted with thetitle of each section and contains ten basic divisions Section I General Section II Limitations Section III Emergency Procedure...

Page 19: ...or or Dealer or refer to the latest revision of BEECHCRAFT Service Instructions No 0250 010 Beech Aircraft Corporation expressly reserves the right to supersede cancel and or declare obsolete any part part numbers kits or publication that may be referenced in this handbook without prior notice The ownerloperator should always refer to all supplements whether STC Supplements or Beech Supplements fo...

Page 20: ...e On the Log page is a listing of the supple mental equipment available for installation on the BEECH CRAFT airplane Upon receipt of a new or revised supplement compare the Log page just received with the existing Log page in the manual Retain the Log page with the latest date on the bottom of the page this log will usually have the greater number of entries and discard the other log VENDOR ISSUED...

Page 21: ...BEECHCRAFT Sundowner 180 Section I C23 M 1285 and After General 25 9 S 3 14 6 4 32 9 10 8 76 DIA O r 11 10 THREE VIEW c29 oor io February 1979 1 7 ...

Page 22: ...fter GROUND TURNING CLEARANCE Radius for Wing Tip 23 ft 11 in Radius for Nose Wheel 9 ft 10 in Radius for inside Gear 2 ft O in Radius for Outside Gear 13 ft O in TURNING RADII ARE CALCULATED USING FULL STEER ING ONE BRAKE AND PARTIAL POWER 1 8 February 1979 ...

Page 23: ...BEECHCRAFTSundowner180 Sectioni C23 M 1285 and After General 14 6 4 32 9 10 8 76 DIA 11 10 i THREE VIEW C23 607 10 February 1979 1 7 ...

Page 24: ... After GROUND TURNING CLEARANCE Radius for Wing Tip 23 ft 11 in Radius for Nose Wheel 9 ft 10 in Radius for inside Gear 2 ft O in Radius for Outside Gear 13 ft O in TURNING RADII ARE CALCULATED USING FULL STEER ING ONE BRAKE AND PARTIAL POWER 1 8 February 1979 ...

Page 25: ...co Lycoming O 360 A2G O 360 A4G O 360 A4J or O 360 A4K engine rated at 180 horsepower Take off and maximum continuous operation sea level 2700 rpm full throttle Engine cooling has been demonstrated for a 100 F day PROPELLER Sensenich M76EMMS O 60 or 76EM8S5 0 60 fixed pitch two blade propeller Static rpm at maximum per missible throttle settings Not over 2350 rpm and not under 2250 rpm No addition...

Page 26: ...gallons usable Each tank has provisions for partial filling to 20 gallons each tank 37 4 gallons usable 15 gallons each tank 27 4 gallons usable Value given is nominal Tank capacity will vary with temperature and manufacturing tolerances OIL CAPACITY The oil capacity is 8 quarts APPROVED O L TYPES Avco Lycoming Specification Number 301 E approves for use lubricating oils which conform to both MIL ...

Page 27: ...mum Landing Weight 2030 lbs ALL CONF GURATIONS Maximum Zero Fuel Weight No Structural Limit Maximum Weight in Baggage Compartment 270 Ibs CABIN AND ENTRY DIMENSIONS Length maximum 7 ft 11 in Height maximum 4 ft O in Width maximum 3 ft 8 in Cabin Door 36 in wide by 38 in high BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Volume 19 5 cu ft Door Width Minimum 23 6 in Door Height Minimum 18 5 in SPEC...

Page 28: ...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 when corrected for instrument error IAS values pubilshed in this handbook assume zero instrument error KCAS Calibrated Airspeed express...

Page 29: ...s the or VC 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 Climb Speed is the airspeed which delivers the greatest gain of altitude in t...

Page 30: ...s the free air static temperature obtained either from inflight temperature indica tions adjusted for instrument error and compressibility effects or ground meteorological sources Indicated The number actually read from an Pressure altimeter when the barometric sub Altitude scale has been set to 29 92 in Hg 1013 2 millibars Pressure Altitude measured from standard Altitude sea level pressure 29 92...

Page 31: ...ating Maximum not limited by time Continuous ENGINE CONTROLS AND INSTRUMENTS Throttle Used to control power by intro Control ducing fuel air mixture into the intake passages of the engine Mixture This control is used to set fuel Control flow in all modes of operation and cuts off fuel completely for engine shut down EGT This indicator is used to identify Exhaust Gas the lean and best power fuel Te...

Page 32: ...the airplane during take off and land ing was actually demonstrated during certification tests MEA Minimum enroute IFR altitude Route A part of a route Each end of that Segment part is identified by 1 a geograph ical location or 2 a point at which a definite radio fix can be established GPH U S Gallons per hour PPH Pounds per hour WEIGHT AND BALANCE TERMINOLOGY Reference An imaginary vertical plan...

Page 33: ...s found C G by dividing the total moment by the total weight of the airplane C G Arm The arm obtained by adding the air plane s individual moments and dividing the sum by the total weight C G Limits The extreme center of gravity loca tions within which the airplane must be operated at a given weight Usable Fuel Fuel available for flight planning Unusable Fuel remaining after a runout test Fuel has...

Page 34: ... Maximum weight approved for the Take off start of the take off run Weight Maximum Maximum weight approved for the Landing landing touchdown Weight Zero Fuel Weight exclusive of usable fuel Weight Tare The weight of chocks blocks stands etc used on the scales when weighing an airplane Leveling Those points which are used during the Points weighing process to level the airplane Jack Points on the a...

Page 35: ...ations 2 5 Propeller Specifications 2 5 Power Plant Instrument Markings 2 6 Oil Temperature 2 6 Oil Pressure 2 6 Fuel Pressure 2 6 Tachometer 2 6 Miscellaneous instrument Markings 2 6 Instrument Air 2 6 Fuel Quantity 2 7 Weight Limits 2 7 Normal Category 2 7 Utility Acrobatic Category 2 7 Center ofGravity Limits 2 7 Normal Category 2 7 Utility Acrobatic Category 2 8 Reference Datum 2 8 Maneuver Li...

Page 36: ...8 Acrobatic Category 2030 Pounds 2 8 Flight Load Factors 2 9 Normal Category 2450 Pounds 2 9 Utility Category 2030 Pounds 2 9 Acrobatic Category 2030 Pounds 2 9 Minimum Flight Crew 2 9 Kinds of Operation Limits 2 9 Required Equipment for Various Conditions of Flight 2 9 Legend 2 11 Fuel Total Fuel 2 19 Fuel Management 2 19 Placards 2 20 2 2 February 1979 ...

Page 37: ...3 IAL SPEED KNOTS MPH KNOTS MPH REMARKS Never Exceed 152 175 152 175 Do not exceed VNE this speed in any operation Maximum 136 156 136 156 Do not exceed Structural this speed Cruising except in smooth VNO or VC air and then only with caution Maneuvering 118 136 118 136 Do not make full VA or abrupt control movements above this speed Maximum 96 110 96 110 Do not extend Flap flaps or operate Extensi...

Page 38: ...36 71 156 61 136 70 156 Range Yellow 136 152 156 175 136 152 156 175 Operate With Arc Caution Only in Smooth Air Red 152 175 152 175 Maximum Line Speed For AII Operations The limits of the arcs on the airspeed indicator are marked in CAS values M 1285 thru M 1586 M 1587 and after POWER PLANT LIMITATIONS ENGINE One Avco Lycoming engine model O 360 A2G O 360 A4G O 360 A4J or O 360 A4K engine rated a...

Page 39: ...r 100 green or 100LL blue FUEL ADDITIVES Alcor TCP Concentrate mixed accordingto the instructions provided by Alcor Inc OIL SPEC FICATIONS Avco Lycoming Specification Number 301E approves for use lubricating oils which conform to both MIL L 6082B straight mineral type and MIL L 22851 ashless dispersant lubricants for airplane engines Refer to the Approved Engine Oils table in the HANDLING SERVICIN...

Page 40: ... Line 245 F OIL PRESSURE Minimum Pressure Red Line 25 psi Minimum Pressure Yellow Arc 25 to 60 psi Operating Range Green Arc 60 to 90 psi Maximum Pressure Red Line 100 psi FUEL PRESSURE Operating Range Green Arc 0 5 to 6 0 psi TACHOMETER Engine Warm up 1000 to 1200 rpm Restricted Operation for O 360 A2G engine only Red Arc 2150 to 2350 rpm Normal Operating Range all engines Green Arc 1800 to 2700 ...

Page 41: ...ff and Landing Weight 2450 lbs Zero Fuel Weight No Structural Limitation Maximum Baggage Compartment Load 270 lbs UTILITY ACROBATICCATEGORY Maximum Ramp Weight 2035 lbs Maximum Take off and LandingWeight 2030Ibs Zero Fuel Weight No Structural Limitation Maximum Baggage Compartment Load Utility Category Only 270 Ibsi CENTER OF GRAVITY LIMITS NORMAL CATEGORY Forward 107 8 inches aft of datum to 1800...

Page 42: ...robatic Category Maximum slip duration is 30 seconds NORMAL CATEGÓRY 2450 POUNDS No acrobatic maneuvers approved UTILITY CATEGORY 2030 POUNDS No acrobatic maneuvers are approved except those listed below MANEUVER ENTRY SPEED CAS Chandelle 116 kts 133 mph Steep Turn 116 kts 133 mph Lazy Eight 116 kts 133 mph Stall Except Whip Use slow deceleration Intentional Spins M 1494 and after only if certific...

Page 43: ...neuvering load factor Flaps Up 6 0 3 0 Flaps Down 2 0 MINIMUM FLIGHT CREW One 1 Pilot KINDS OF OPERATION LIMITS 1 VFR day and night 2 IFR day and night REQUIRED EQUIPMENT FOR VARIOUS CONDITIONS OF FLIGHT Federal Aviation Regulations 91 3 a 91 24 91 25 91 32 91 33 91 52 91 90 91 97 91 170 specifý the minimum numbers and typesof airplane instruments and equipment which must be installed and operable...

Page 44: ...o maintain airworthiness can permit continued or uninterrupted operation of the airplane temporarily For the sake of brevity the Required Equipment Listing does not include obviously required items such as wings rudders flaps engine landing gear etc Also the list does not include items which do not affect the airworthiness of the airplane such as entertainment systems passenger convenience items e...

Page 45: ...N ICING CONDITIONS PROHIBITED LEGEND Numbers refer to quantities required to be operative for a specified condition lndicates that the item may be inoperative for the specified condition Refer to the REMARKS AND OR EXCEPT10NS column for explicit information or reference February 1979 2 11 ...

Page 46: ...Exceptions GENERAL Overwater flight Per FAR 91 33 m COMMUNICATIONS m VHF communications system Per FAR 91 33 ELECTRICALPOWER Battery 1 1 1 1 m DC alternator 1 1 1 1 Starter Engaged 1 1 1 1 May be inoperative Warning Light provided ammeter is o M 2278 and after operative and monitored ...

Page 47: ...MENT AND FURNISHING m Seat belts and 1 1 1 1 Per Person or Per FAR 91 33 O C Shoulder harness y Emergency locator trans 1 1 1 1 Per FAR 91 52 o mitter O o FIRE PROTECTION Portable fire extinguisher Optional ...

Page 48: ...icator 1 1 1 1 May be inoperative for ferry flight m provided tabs are visually checked m in the neutral position prior to I take off and checked for full range of operation Flap position indicator 1 1 1 1 May be inoperative provided flap I On electric f lap system travel is visually inspected prior to take off œ Stall warning 1 1 1 1 o ...

Page 49: ...ty indicator 2 2 2 2 One may be inoperative pro vided other side is operational and amount of fuel on board can o be established to be adequate for the intended flight Fuel pressure indicator 1 1 1 1 m o ICE AND RAIN PROTECTION Emergency static Optional air source Pitot heater 1 1 Optional oi e ...

Page 50: ... o an Vor FR Day COMPON ENT IFR Night Remarks and or Exceptions LIGHTS Cockpit and instrument Lights must be operative lights Taxi light N o Landing light Per FAR 91 33 i Rotating beacon 1 1 Optional I Position light 3 3 y Ë o ...

Page 51: ... 1 1 1 i 2 Vertical speed i Magnetic compass 1 1 1 1 g Attitude indicator 1 1 e Turn coordinator 1 1 Directional gyro 1 1 Clock 1 1 m Transponder Per FAR 91 24 91 90 91 97 Navigation equipment Per FAR 91 33 VACUUM r Vacuum system for 1 1 f n instrument air to Vacuum gage 1 1 ...

Page 52: ...OMPONENT Remarks and or Exceptions ENGINE INDICATING INSTRUMENTS o Engine tachometer indicator 1 1 1 1 m m Exhaust gas temperature Optional o indicator ENGINE OIL g INSTRUMENTS o Oil pressure indicator 1 1 1 1 a Oil temperature indicator 1 1 1 1 to 1 o ...

Page 53: ...after Two 29 9 gallon tanks in wings with a total of 57 2 gallons usable Value given is nominal Tank capacity will vary with temperature and manufacturing tolerances FUEL MANAGEMENT On M 1517 thru M 1879 except M 1875 and prior air planes if service Instruction No 0624 281 is ac complished Do not take off when the Fuel Quantity Gages indicate in the Yellow Band or with less than 11 gallons in each...

Page 54: ...NG INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR FLAPS UP 3 8 1 9 DOWN 1 9 MAXIMUM MANEUVERING PEED 136 MPH NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED UTILITYCATEGORY MAXIMUM DESIGN WEIGHT 2030 LBS REFER TO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR FLAPS UP 44 2 2 DOWN 2 2 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW MANEUVER MAXIMUM ENTRY SPEE...

Page 55: ...TATIONSSTATEDIN THE FORM OF PLACARDS MARKINGS AND MANUALS NORMAL CATEGORY MAXIMUM DESIGN WEIGHT 2450 LBS REFER TO WEIGHf AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR FLAPS UP 3 8 1 9 DOWN 1 9 MAXIMUM MANEUVERING SPEED 118 KTS 136 MPH NO ACROBATICMANEUVERS INCLUDING SPINS APPROVED UTILITYCATEGORY MAXIMUM DESIGN WEIGHT 2030 LBS REFER TO WEIGHT AND BALANCE DATA FOR LOADING...

Page 56: ... APPROVED UTILITY ACROBATIC CATEGORY MAXIMUM DESIGN WEIGHT 2030 LES REFERTO WEIGHT AND BALANCE DATA FOR LOADING INSTRUCTIONS FLIGHT MANEUVERING LOAD FACTOR FLAPS UP i 6 0 3 0 DOWN E2 0 NO ACROBAT1C MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW MANEUVER MAX1MUM ENTRY SPEED CHANDELLES 133 MPH LAZY EIGHTS 133 MPH STEEP TURNS 133 MPH STALLS EXCEPT WHIP STALLSI SLOW DECELERATION NOTE MAXIMUM ALTITUDE LO...

Page 57: ...G INSTRUCTIONS FLIGHTMANEUVERING LOAD FACTOR FLAPS UP 6 0 30 DOWN 2 0 NO ACROBATIC MANEUVERSAPPROVED EXCEPT THOSE LISTED BELOW MANEUVER MAXIMUM ENTRY SPEED CHANDELLES 116 KTS 133 MPH LAZY EIGHTS 116 KTS 133 MPH STEEPTURNS 116 KTS 133 MPH STALLSlEXCEPTWHIP STALLS SLOW DECELERATION NOTE MAXIMUM ALTiTUDE LOSS DURING STALL 300 FT SPINS IFOR OPERATIONAL LIMITATIONSSEE PLACARD ON UN VISOR RECOMMENDED EN...

Page 58: ...FECTIVENESS On Flap Extension Handle M 1285 thru M 1979 except M 1971 CAS FLAPSPULL TO EXTEND MAX SPEED 110 MPH RETRACTED 0 FIRSTNOTCH 15 SECOND NOTCH 25 THIRD NOTCH 35 On Flap Extension Handle M 1971 M 1980 and after CAS FLAPS PULL TO EXTEND MAX SPEED 96 KTS 110 MPH RETRACTED 0 FIR TNOTCH 15 SECOND NOTCH 25 THIRO NOTCH 35 2 24 February 1979 ...

Page 59: ...NTROLS AND EXEEUTE ASMOOTH PULLOUT ALLERONS SHOUID LE NEUTRAL AND THROTTLE 1N lOLE POSlflON AT ALL TIMES DURING RECOVERY The above placard reads as follows OPERATIONAL LIMITATIONSSPINS The airplane willnot spin if orthodoxentry is used but willenter a spiral dive Speed builds up rapidly in a spiral dive requiring high pullout loads therefore if a spiral is inadvertently entered recovery from the s...

Page 60: ...fter PLACARDS On Fuel Selector Panel M 1285 through M 1516 L TANK R TANK 29 GAL 29 GAL OFF On Fuel Selector Panel M 1517 through M 1879 except M 1875 or prior airplanes after cornplíance with Service Instructions No 0624 281 L TANA TANAL OFF OFF 2 26 February 1979 ...

Page 61: ...ctions No 1095 OFF Adjacent to Engíne Instrument Cluster M 1517 through M 1879 except M 1875 orprior airplanes after complíance with Service Instructions No 0624 281 DO NOT TAKE OFF WHEN FUEL OUANTITY GAUGE INDICATES IN YELLOW OR WITH LESS THAN H GALLONS IN EACH MAIN TANK MAXIMUM LIP DURATION IS 30 5tcDNDS Adjacent to Engine Instrument Cluster M 1875 M 1880 and after DO NOT TAKE OFF WHEN FUEL QUAN...

Page 62: ...12 and M 1415 M 1419 M 1423 M 1439 and M 1447 oPEN On Left Cabin Door Acrobatic e o EMERGENCYEXIT TURN HANDLE CLOCKWISE PULL LATCHABOVE ARM REST THEN KICK OUT TO JETTISON DOOR On Right Cabin Door Acrobatic De EMERGENCYEXIT TURN HANDLE COUNTER CLOCKWISE PULL LATCH ABOVE ARM REST THEN KICK OUT TO JETTISON DOOR 2 28 August 1980 ...

Page 63: ...IRCRAFT LEVEL BAGGAGE COMPARTMENT FLOOR On Pedestal Between Front Seats D O w r NO N O s E U P I On Second Window Frame Right Side M 1658andafteras required by weight and balance data BAGGAGE CARGO OR FAMILYSEATS I LOAD IN ACCORDANCE WITH WEIGHT BALANCE DATA MAXIMUMSEAT CAPACITY POUNDS February 1979 2 29 ...

Page 64: ... CALIBRATION ERROR ON EMERGENCY or o WARNING o EMERGENCY AIRSPEED STATIC SOURCE ON EMERGENCY SEE PILOTS CHECK LIST OR FLLGHT MANUAL EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER CALLBRATION ERROR OFF NORMAL Of wARNING o EMERGENCY AIRSPEED STATICSOURCE EMERGENCY ON SEE PILOTS CHECK LIST I y OR FLIGHT MANUAL OFF EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER NORMAL CALIBRATION ERROR On Aft Cabin Bulkhead...

Page 65: ... Aft Corner of Each Cabin Door when installed NSTRUCTIONS SHOULDER STRA l OCCUPANT SHORTER THAN 4FT 71N DO NOT USE SHOULDER STRAP 2 NEVER USE SHOULDER STRAP WITH OUT LAP BELTS or INSTRUCTION SHOULDER STRAP l OCCUPANTS SHORTER THAN 4 FT 7 IN DO NOT USE SHOULDER STRAP 2 PLACE SEAT BACK IN THE UPRIGHT POSITION DURING TAKEOFF AND LANDING February 1979 2 31 ...

Page 66: ...Section11 BEECHCRAFTSundowner180 Limitations C23 M 1285 and After INTENTIONALLY LEFT BLANK 2 32 February 1979 ...

Page 67: ...ng Engine 3 5 Condition Loss OfEngine Power 3 5 Airstart Procedure 3 6 Engine Fire In Flight 3 6 On The Ground 3 7 Emergency Descent 3 7 Maximum GlideConfiguration 3 7 Landing Emergencies Landing Without Power 3 7 Systems Emergencies 3 8 Starter Energized Warning Light Illuminated 3 8 Alternator OutProced ure 3 8 Unscheduled Electric StabilatorTrim 3 9 Emergency Static AirSource System 3 9 Unlatch...

Page 68: ...Section III BEECH CRAFT Sundowner 180 Emergency Procedures C23 M 1285 and After INTENTIONALLY LEFT BLANK 3 2 February 1979 ...

Page 69: ...ctor stop minimizes the possibility of inadvertently turning the fuel selector valve to the OFF detent position The stop is a spring which must be depressed before the selector valve handle can be rotated to the OFF position The following information is presented to enable the pilot to form in advance a definite plan of action for coping with the most probable emergency situations which could occu...

Page 70: ...4 Battery Switch Alternator Switch and Fuel Boost Switch OFF 5 Magneto Start Switch OFF AFTER LIFTOFF AND IN FLIGHT Landing straight ahead is usually advisable sufficient altitude is available for maneuvering accomplish the following 1 Mixture FULL RICH then LEAN as required 2 Fuel Boost Pump ON 3 Fuel Selector Valve SELECT OTHER TANK Check to feel detent and check visually 4 Magnetos CHECK LEFT a...

Page 71: ...sired flaps before securing battery When certain of reaching the selected landing site 7 Airspeed 68 kts 78 mph 8 Flaps AS REQUIRED ENGINE DISCREPANCY CHECKS CONDITION ROUGH RUNN NG ENGINE 1 Mixture FULL RICH then LEAN as required 2 Magneto Start Switch CHECK LEFT and RIGHT then BOTH CONDITION LOSS OF ENGINE POVVER 1 Fuel Pressure Gage CHECK If fuel flow is abnormal y low a Mixture FULL RICH b Fue...

Page 72: ...4 Fuel Boost Pump ON until power is regained then OFF Leave on if engine driven fuel pump is inoperative 5 Throttle ADJUST to desired power 6 Mixture LEAN as required ENGINE FIRE IN FLIGHT The red ventilation controls must be closed to shut off all heating system outlets so that smoke and fumes will not enter the cabin The control labeled CABIN AIR must be pulled out to close The control labeled D...

Page 73: ...hes OFF 5 Extinguish with Fire Extinguisher EMERGENCY DESCENT 1 Throttle IDLE 2 Airspeed ESTABLISH 152 kts 175 mph MAXIMUM GLIDE CONFIGURATION 1 Flaps UP 2 Airspeed 78 kts 90 mph Glide distance is approximately 1 7 nautical miles 2 statute miles per 1000 feet of altitude above the terrain LANDING EMERGENCIES LANDINGWITHOUT POWER When assured of reaching the landing site selected and on final appro...

Page 74: ...tarter and it remains engaged Continuing to supply power to the starter will eventually result in the complete loss of electrical system power substantial starter damage and possible damage to other electrical system components If light remains i uminated on the ground 1 Battery Switch and Alternator Switch OFF 2 Do Not Take Off light remains i uminated in flight after air start 1 Battery Switch a...

Page 75: ...im Thumb Switch On Control Wheel MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM to open circuit breaker 3 Stabilator Trim ON OFF Switch On Instrument Panel OFF 4 Manual Stabilator Trim Control Wheel RETRIM AS DESIRED EMERGENCY STATIC AIR SOURCE SYSTEM THE EMERGENCY STATIC AIR SOURCE SHOULD BE USED FOR CONDITIONS WHERE THE NORMAL STATIC SOURCE HAS BEEN OBSTRUCTED When the airplane has been expos...

Page 76: ...when system is not needed UNLATCHED DOOR IN FLIGHT if the cabin door is not locked it may come uniatched in flight This may occur during or just after take off The door will trail in a position approximately 3 inches open A buffet may be encountered with the door open in flight Return to the field in a normal manner If practicable during the landing flare out have a passenger hold the door to prev...

Page 77: ...0 to the horizon apply full aileron against the intended direction of spin The airplane will go slightly inverted and enter a normal spin If aileron against the direction of spin is not applied or applied too late the airplane will enter a rapid spiral dive and recovery must be initiated by the second turn If the full back stick is not applied and held the airplane may spiral Again recovery must b...

Page 78: ...Section III BEECH CRAFT Sundowner 180 Emergency Procedures C23 M 1285 and After INTENTIONALLY LEFT BLANK 3 12 February 1979 ...

Page 79: ... 4 7 After Starting And Taxi 4 8 Before Takeoff 4 8 Takeoff 4 9 Climb 4 10 Cruise 4 10 Leaning Using the Exhaust Gas Temperature Indicator EGT 4 10 Descent 4 11 Before Landing 4 11 Balked Land ing 4 12 After Landing 4 12 Shutdown 4 12 Environmental Systems 4 12 Heating and Ventilation 4 12 Cold Weather Operation 4 13 Pref light Inspection 4 13 Engine 4 13 Icing Conditions 4 14 Engine Break In Info...

Page 80: ...Section IV BEECH CRAFT Sundowner 180 Normal Procedures C23 M 1285 and After INTENTIONALLY LEFT BLANK 4 2 February 1979 ...

Page 81: ...ERATION Take off Lift off 65 Knots 75 mph 50 Ft 74 Knots 85 mph Maximum Climb Best Rate Vy 75 Knots 86 mph Best Angle v 69 Knots 79 mph Cruise Climb 82 Knots 95 mph Maximum Turbulent Air Penetration 118 Knots 136 mph Balked Landing 64 Knots 74 mph Landing Approach 68 Knots 78 mph Maximum Demonstrated Crosswind 17 Knots 20 mph B19 604 10 February 1979 4 3 ...

Page 82: ...CTED c Aileron CHECK d Wing Tip CHECK e Position Light CHECK 3 LEFT WING LEADING EDGE a Pitot Tube CHECK Remove Cover b Landing Light CHECK c Tie Down and Chocks REMOVE d Stall Warning CHECK for movement of vane e Fuel Tank CHECK QUANTITY Filler Cap SECURE 4 LEFT LANDING GEAR a Tire and Brake CHECK b Fuel Sump DRAIN 5 NOSE SECTION a Left Cowl SECURE b Induction Air Intake CLEAR Filter CHECK for co...

Page 83: ...Wing Tip CHECK e Position Light CHECK 8 R GHT WlNG TRA L NG EDGE a Aileron CHECK b Flap CHECK c Fuel Tank Vent Line UNOBSTRUCTED 9 R GHT FUSELAGE a Static Pressure Button UNOBSTRUCTED b Emergency Locator Transmitter ARMED 10 EMPENNAGE a Control Surfaces CHECK b Tie Down REMOVE c Position Light CHECK 11 LEFT FUSELAGE a Static Pressure Button UNOBSTRUCTED b All Antennas CHECK c Baggage Door CHECK BE...

Page 84: ...er or on airplanes which have complied with BEECHCRAFT S I No 1095 a fuel selector stop has been added to the selector valve guard The fuel selector stop minimizes the possibility of inadvertently turning the fuel selector valve to the OFF detent position The stop is a spring which must be depressed before the selector valve handle can be rotated to the OFF position WARNING Do not take off if eith...

Page 85: ...to 14 25 volts for 14 volt system and 27 75 to 28 25 volts for 28 volt system 4 Auxiliary Power Unit ON 5 Engine START using normal procedures 6 Auxiliary Power Unit OFF after engine has been started 7 Auxiliary Power Unit DISCONNECT 8 Alternator Switch ON STARTING CAUTION Vernier type engine controls should not be rotated clockwise after being advanced to the full forward position 1 Mixture FULL ...

Page 86: ...ammeter indication is less than 25 of full charge at 1000 to 1200 rpm within two minutes with no additional electrical equipment on If not turn off the Battery Switch and Alternator Switch and do not take off 6 External Power if used OFF DISCONNECT 7 ALT alternator switch ON 8 Oil Pressure ABOVE RED RADIAL WITHIN 30 SECONDS 9 Warm up 1000 to 1200 RPM 10 All Engine Indicators CHECK 11 Fuel Boost Pu...

Page 87: ... 2200 RPM 8 Magnetos CHECK at 2200 rpm maximum drop of 125 rpm on each magneto variance between individual magnetos should not exceed 50 rpm 9 Carburetor Heat CHECK Set cold for takeoff 10 Throule FAST IDLE 11 Stabilator Trim TAKE OFF RANGE Green White or Black Band 12 Flaps CHECK and SET 13 Controls CHECK FREE and for proper direction of travel 14 Fuel Boost Pump ON 15 Mixture FULL RICH or as req...

Page 88: ...xture LEAN AS REQUIRED tighten friction on push pull type control LEANING USING THE EXHAUST GAS TEMPERATURE INDICATOR EGT For level flight at 75 power or less the EGT unit should be used in the following manner 1 Lean the mixture and note the point on the indicator that the temperature peaks and starts to fall a CRUISE LEAN MIXTURE Enrich mixture until the EGT shows a drop of 25 F below peak on th...

Page 89: ...AS REQUIRED BEFORE LANDING 1 Seat Belts and Shoulder Harnesses SECURE NOTE All reclining seats must be in the upright position during landing 2 Fuel Selector Valve SELECT TANK MORE NEARLY FULL feel for detent and check visually 3 Mixture FULL RICH or as required by field elevation tighten friction on push pull type control 4 Landing Light AS REQUIRED 5 Flaps DOWN maximum extension speed 96 kts 110...

Page 90: ...AFTER LANDING 1 Landing and Taxi Lights AS REQUIRED 2 Flaps UP 3 Trim Tab SET TO 0 SHUTDOWN 1 Brakes SET 2 Fuel Boost Pump OFF 3 Electrical and Avionics Equipment OFF 4 Throttle CLOSE 5 Mixture IDLE CUT OFF 6 Magneto Start Switch OFF after engine stops 7 Battery Switch OFF 8 Alternator Switch OFF 9 Control Lock INSTALL if conditions warrant 10 Install wheel chocks and release brakes if the airplan...

Page 91: ... disturb or completely destroy the de signed aerodynamic properties of the airfoils The normal preflight procedures should then be com pleted with particular attention given to check of flight controls for complete freedom of movement ENGINE Use engine oil in accordance with Consumable Materials in the HANDLING SERVICING AND MAINTENANCE Section WARNING Ascertain that magneto switch and battery mas...

Page 92: ...il should be drained while the engine is hot and stored in a warm area until the next flight If there is no oil pressure within the first 30 seconds of running or if oil pressure drops after a few minutes of ground operation shut down and check for broken oil lines oil cooler leaks or the possibility of congealed oil NOTE It is advisable to use external power for start ing in cold weather During w...

Page 93: ...t above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations NOTE The preceding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions or where in the pilot s judgement an altitude of less than 2000 feet is necessary to adequately exercise his duty to see and evo...

Page 94: ......

Page 95: ...ration Normal System 5 8 Airspeed Calibration Alternate System 5 9 Altimeter Correction Normal System 5 10 Altimeter Correction Alternate System 5 11 Power Off Stall Speeds 5 12 Wind Components 5 13 Take Off Distance Hard Surface 5 14 Take Off Distance Grass Surface 5 15 Normal Climb 5 16 Time Fuel and Distance to Climb 5 17 Cruise Performance 5 18 Landing Distance Hard Surface 5 20 Landing Distan...

Page 96: ...Section V BEECHCRAFT Sundowner 180 Performance C23 M 1285 and After INTENTIONALLY LEFT BLANK 5 2 February 1979 ...

Page 97: ...examples and calculations assume the following conditions CONDITIONS At Stapleton International DEN Outside Air Temperature 15 C 59 F Field Elevation 5330 ft Altimeter Setting 29 60 in Hg Wind 270 at 10 kts Runway 26L length 10 000 ft i Route of Trip DEN V4 GLD V132 HUT V73 ICT For VFR Cruise at 9 500 feet AVG MAG WIND OAT CRS AVG 9500 9500 ALT ROUTE MAG DIST FEET FEET SETTING SEGMENT VAR NM DIR K...

Page 98: ...t to field elevation for each 1 in Hg below 29 92 and subtract 100 feet from field elevation for each 1 in Hg above 29 92 Pressure Altitude at DEI 29 92 29 60 32 in Hg The pressure altitude at DEN is 320 feet above the field elevation 5330 320 5650 ft Pressure Altitude at ICT 29 92 29 56 36 in Hg The pressure altitude at ICT is 360 feet above the field elevation 1332 360 1692 ft NOTE For flight pl...

Page 99: ...GPH KNOTS 9500 2662 10 5 123 I Time and fuel used were calculated as follows Time Distance Ground Speed Fuel Used Time Fuel Flow Results are FUEL EST TIME AT USED GROUND CRUISE FOR ROUTE DISTANCE SPEED ALTITUDE CRUISE SEGMENT NM KNOTS HRS MIN GAL DEN TXC 65 117 33 5 8 TXC GLD 73 121 36 6 3 GLD HUT 195 125 1 34 16 4 HUT ICT 33 124 16 2 8 Distance required to climb has been subtracted from segment d...

Page 100: ...minutes 120 knots Reserve Fuel 45 minutes at 57 maximum continuous power Enter the CRUISE POWER SETTINGS table for 57 MCP at 2300 RPM The fuel flow at 57 MCP is 7 8 gallons per hour Reserve fuel 45 min 7 8 GPH 5 9 gallons Total Fuel 34 6 5 9 40 5 gallons The estimated landing weight is determined by subtracting the fuel required for the trip from the ramp weight Assumed ramp weight 2450 lbs Estima...

Page 101: ...ic conditions from which performance parameters have been determined They are not intended to be used as instructions however performance values de termined from charts can only be achieved if specified conditions exist 3 The full amount of usable fuel is available for all approved flight conditions 4 Engine and component cooling has been demon strated for temperatures up to 100 F at sea level wit...

Page 102: ...80 KTS CAS 78 KTS 160 140 FLAPS UP FLAPS DOWN 140 120 140 120 120 120 o 100 100 m100 100 o 80 80 60 60 40 40 40 60 80 100 120 1AO 40 60 80 100 1 lAS INDICATED AIRSPEED KNOTS IAS INDICATED AIRSPEED KNOTS 111111 II III 2 60 80 100 120 140 160 60 80 100 120 140 Og IAS INDICATED AIRSPEED rv MPH IAS INDICATED AlRSPEED o MPH W Q ...

Page 103: ...TS 126 MPH CAS 98 KNOTS 113 MPH STORM WINDOW CLOSED CEis WINE Dal Pi 100 160 140 Q C 160 140 120 110 100 100 so a a so 100 80 80 70 80 60 60 60 E 50 70 90 110 130 1b0 63 83 100 1 0 1tO INDICATED AIRSPEED KNOTS INDICATED AIRSPEED KNOTS i I I I I I I I I I I s i 60 80 100 120 140 160 60 80 100 120 140 160 INDICATED AIRSPEED MPH INDICATED AIRSPEED MPH ...

Page 104: ...SectionV BEECHCRAFTSundowner180 Performance C23 M 1285 and After OOOOO o o S3COlillV 031VDIONI 01 GOV 12001II IV OE1V3IGNI 5 10 February 1979 ...

Page 105: ...BEECHCRAFT Sundowner 180 Section V C23 M 1285andAfter Performance O I 4 a z uJ i u 031VOIONI 01 GOV BGflllllV CB1VOIONI NOH I 10VBIBOS February 1979 5 11 ...

Page 106: ...SPEEDS WE GHT 2450 LBS Maximum altitude loss during a normal stall recovery is approximately 300 ft ANGLE OF BANK LEVEL 30 45 60 FLAPS UP 72 mph 77 mph 85 mph 101 mph 63 kts 67 kts 74 kts 88 kts FLAPS DOWN 35 59 mph 63 mph 70mph 83 mph 51 kts 55 kts 61 kts 72 kts 5 12 February 1979 ...

Page 107: ... Component is 17kts 20mph EXAMPLE WIND SPEED 20 KTS ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH 503 HEADWIND COMPONENT 13 KTS CROSSWIND COMPONENT 15 KTS FLIGHT PATH 40 i 0 10 20 30 0 20 50 60 70 10 80 D 90 100 10 110 140 180 160 150 130 120 170 20 0 10 20 30 4 CROSSWIND COMPONENTS o KNOTS February 1979 5 13 ...

Page 108: ... 13 11 1756 2975 0 59 15 1130 1955 52 11 1293 2224 45 7 1481 2535 38 3 1701 2894 31 1 1957 3311 77 25 1248 2155 70 21 1429 2455 63 17 1640 2002 56 13 1856 3204 49 9 2173 3671 95 35 1373 2369 88 31 1575 2701 81 27 1809 3087 74 23 2083 3535 67 19 2404 4055 23 5 728 1454 16 9 836 1653 9 13 961 1883 2 17 1108 2149 6 21 1279 2466 41 5 813 1618 34 1 935 1842 27 3 1077 2102 20 7 1243 2402 13 11 1438 2750...

Page 109: ...62 11 1396 2327 45 7 1599 2663 38 3 1836 3030 31 1 2113 3467 77 25 1347 2255 70 21 1543 2569 63 17 1771 2933 66 13 2036 3354 49 9 2346 3844 95 35 1482 2478 88 31 1700 2827 81 27 1954 3231 74 23 2249 3701 67 19 2595 4247 23 5 786 1512 16 9 902 1720 9 13 1038 1960 2 17 1196 2237 6 21 1381 2558 41 5 878 1682 34 1 1009 1917 27 3 1163 2187 20 7 1342 2501 13 11 1552 2865 15 69 15 977 1865 52 11 1125 212...

Page 110: ... MIN KTS MPH F C FT MIN KTS MPH 23 5 841 9 13 621 6 21 389 20 29 167 41 5 816 27 3 596 13 11 362 2 19 141 2450 59 15 792 78 90 45 7 572 78 87 31 1 338 74 85 16 9 117 74 85 77 25 769 63 17 549 49 9 315 34 1 94 95 55 747 81 27 527 67 19 293 52 11 72 23 5 1047 9 13 812 6 21 567 20 29 327 p 41 5 1021 27 3 787 13 11 539 2 19 302 Ë g 2200 59 15 997 76 88 45 7 763 74 85 31 1 515 72 8Š 16 9 277 72 83 g 77...

Page 111: ...DE 5650 FT MIXTURE LEAN TO MAXIMUM RPM CRUISE ALTITUDE 9500 FT THEN ENRICH SLIGHTLY TIME TO CLIMB 20 9 11 MIN FLAPS UP FUEL TO CLIMB 3 9 1 9 2 GAL WEIGHT 2450 LBS DIST TO CLIMB 27 12 15 NM STANDARD DAY 78 KTS 90 MPH 10 8 o O 10 20 33 TIME TO CLIMB MINUTES I I I I I I 01 2 3 4 5 FUEL TO CLIMB GALLONS l III I I O 10 20 30 40 DISTANCE TO CLIMB NAUTICAL MILES February 1979 5 17 ...

Page 112: ... 5 126 145 298 497 4500 2500 70 9 8 116 133 346 581 2300 59 8 0 105 121 381 641 2696 82 12 0 126 145 308 517 5500 2500 68 9 6 116 133 352 593 2300 58 7 9 104 120 382 644 2688 79 11 6 125 144 318 534 6500 2500 67 9 4 115 132 359 606 2300 58 7 9 103 119 379 640 2680 77 11 2 124 143 324 546 7500 2500 66 9 2 115 132 365 616 2300 57 7 9 102 117 378 638 2670 75 10 8 124 143 335 564 8500 2500 65 9 0 114 ...

Page 113: ...ank 4 Determination of in flight fuel flow Enter the table at the altitude nearest to the computed density altitude and read the fuel flow for the TAS value presented that is nearest to the actual true airspeed ASSOCIATED CONDITIONS Pressure Altitude 4500 FEET OAT 53 F Indicated Airspeed 111 KTS EXAMPLE Density Altitude 5200 FEET Actual True Airspeed 121 KTS Nearest Altitude on Table 5500 FEET Int...

Page 114: ...7 38 3 840 1691 31 1 894 1776 77 25 727 1521 70 21 771 1587 63 17 819 1658 56 13 871 1740 49 9 926 1827 95 35 751 1558 88 31 798 1626 81 27 847 1703 74 23 901 1788 67 19 959 1882 23 5 496 1190 16 9 530 1243 9 13 567 1302 2 17 607 1365 6 21 650 1431 41 5 518 1222 34 1 553 1280 27 3 692 1342 20 7 634 1407 13 11 679 1476 15 59 15 539 1257 52 11 676 1317 45 7 617 1381 38 3 661 1448 31 1 708 1520 i 77 ...

Page 115: ...1675 45 7 925 1751 38 3 983 1834 31 1 1046 1927 77 25 851 1644 70 21 903 1719 63 17 959 1797 56 13 1019 1888 49 9 1084 1985 95 35 879 1685 88 31 933 1762 81 27 992 1847 74 23 1054 1941 67 19 1122 2045 23 5 581 1274 16 9 62T 1333 9 13 663 1399 2 17 710 1468 6 21 760 1542 41 5 606 1310 34 1 647 1374 27 3 693 1442 20 7 741 1515 13 11 794 1591 15 59 15 631 1349 52 11 674 1415 46 7 722 1486 38 3 773 15...

Page 116: ...Section V BEECHCRAFT Sundowner 180 Performance C23 M 1285 and After INTENTIONALLY LEFT BLANK 5 22 January 1982 ...

Page 117: ...alance Form 6 7 Weight And Balance Record 6 9 Weight And Balance Responsibilities 6 11 Gross Weight Moment Limits Graph 6 12 Gross Weight Moment Limits 6 12 Computing Procedure 6 15 Sample Weight And Balance Loading Form 6 16 Weight And Balance Loading Form 6 17 Useful Load Weights And Moments Occupants 6 18 Oil 6 19 Usable Fuel 6 19 Baggage 6 20 Equipment List Provided For Each Airplane February ...

Page 118: ...Section VI BEECHCRAFT Sundowner 180 Wt and Bagquip List C23 M 1285 and After INTENTIONALLY LEFT BLANK 6 2 February 1979 ...

Page 119: ...ised a form called Basic Empty Weight and Balance When the air plane is delivered from the factory it will first be weighed and the data recorded on this form Provision has been made on the form for listing additions of items to be installed before the delivery or subtractions of items to be removed before delivery from the as weighed condition This then represents the empty weight of the airplane...

Page 120: ...wing front spar at Fuselage Station 129 4 and one on the aft fuselage at Fuselage Station 285 9 tail tie down ring 2 Fuel should be drained preparatory to weighing Tanks are drained from the regular drain ports with the airplane in static ground attitude The unusable fuel to be added to a Basic Empty Weight is 6 Ibs M 1285 thru M 1516 at Fuselage Station 125 0 45 6 lbs M 1517 thru M 1879 except M ...

Page 121: ...o the other All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselage centerline The locations of the wheel reactions will be approximately at Fuselage Station 134 0 for main wheels and Fuselage Station 58 5 for A 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 gr...

Page 122: ...Section VI BEECHCRAFT Sundowner 180 Wt and BaWquipList C23 M 1285 and After 2 O e 6 oo go o 2 0 I Lu 0 6 o o O I OW 6 6 February 1979 ...

Page 123: ... È LEFT MAIN RIGHT MAIN NOSE OR TAIL TOTAL AS WEIGHED Space below provided for additions and subtractions to as weighed condition EMPTY WEIGHT DRY ENGINE OIL 15 0 48 0 720 UNUSABLE FUEL M 1285 thru M 1516 6 0 125 0 750 M 1517 thru M 1879 except M 1875 or prior airplanes after a compliance with S l No 0624 281 45 6 125 0 5700 E st oo o M 1875 M 1880 and after 15 6 125 0 195Q I N BASIC EMPTY WEIGHT ...

Page 124: ...y weight and c g is a suitable means for meeting both requirements The current equipment list and empty weight and c g information must be retained with the airplane when it changes ownership Beech Aircraft Corporation cannot maintain this information the current status is known only to the owner If these papers become lost the FAA will require that the airplane be re weighed to establish the empt...

Page 125: ... AND BALANCE RECORD re m C SERIAL NO REGISTRATION NO PAGE NO WEIGHT CHANGE RUNNING BASIC DATE NO__ DESCRIPTION OF ARTICLE ADDED OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 m o ...

Page 126: ...EIGHT AND BALANCE RECORD SERIAL NO REGISTRATION NO PAGE NO WE GHT CHANGE RUNNING BASIC DATE DESCRIPTION OF ARTICLE ADDED i OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 g ...

Page 127: ... and Moments tables The minimum and maxi mum moments are shown on the Moment Limits vs Weight table and can also be plotted on the Moment Limits vs Weight graph as visual indication thatthe limit is within the operational envelope These moments correspond to the forward and aft center of gravity flight limits for a particular weight The airplane must be loaded in such a manner to keep the center o...

Page 128: ...tion VI BEECH CRAFT Sundowner 180 Wt and Bal Equip List C23 M 1286 and After GROSS WEIGHT MOMENT LIMITSGRAPH oooooooooo ococo ce cm o o o e c4 CO CO 49 cq SGNGOd LHOIEM LAVHORIV GSGVO I 6 12 February 1979 ...

Page 129: ...37 2401 2430 2777 2875 1640 1768 1940 2040 2250 2413 2440 2791 2887 1650 1779 1952 2050 2263 2425 2450 2805 2898 1660 1789 1964 2060 2276 2437 1670 1800 1976 2070 2290 2448 1680 1811 1987 2080 2303 2461 1690 1822 1999 2090 2316 2472 1700 1833 2011 2100 2329 2484 1710 1843 2023 2110 2343 2496 1720 1854 2035 2120 2356 2508 1730 1865 2047 2130 2369 2520 1740 1876 2058 2140 2383 2532 1750 1887 2070 21...

Page 130: ...068 2166 1610 1736 1835 1910 2081 2177 1620 1746 1847 1920 2004 2189 1630 1757 1858 1930 2107 2200 1640 1768 1870 1940 2120 i 2212 1650 1779 1881 1950 2133 2223 1660 1789 1892 1960 2145 2234 1670 1800 1904 1970 2158 2246 1680 1811 1915 1980 2172 2257 1690 1822 1927 1990 2185 2269 1700 1833 1938 2000 2198 2280 1710 1843 1949 2010 2211 2291 1720 1854 1961 2020 2224 2303 1730 1865 1972 2030 2237 2314...

Page 131: ...red for start taxi and take off Add the Fuel to Zero Fuel Condition to obtain the SUB TOTAL Ramp Condition 5 Subtract the fuel to be used for start taxi and take off to arrive at the SUB TOTAL Take off Condition 6 Subtract the weight and moment of the fuel in the incremental sequence in which it is to be used from the take off weight and moment The Zero Fuel Condi tion the Take Off Condition and t...

Page 132: ... NXXX ITEM WEIGHT MOM 100 1 BASIC EMPTY CONDITION 1500 1650 2 FRONT SEAT OCCUPANTS 340 374 3 3rd 4th SEAT OCCUPANTS 340 482 4 BAGGAGE OR CARGO 40 67 5 SUB TOTAL ZERO FUEL CONDITION 2220 2573 6 FUEL LOADING 37 GAL 222 259 7 SUB TOTAL RAMP CONDITIO 2442 2832 8 LESS FUEL i TAXI AND TA FF 5 6 9 SUB TOTAL TAKE OFF CONDITION 2437 2826 10 LESS FUEL TO DESTINAT10N 25 GAL 150 176 11 LANDING CONDITION 2287 ...

Page 133: ... SEAT OCCUPANTS gg6 3ZÚ 3 3rd 4th SEAT OCCUPANTS so5 46o 4 BAGGAGE OR CARGO 30 60 5 SUB TOTAL ZERO FUEL CONDITION 2270 25 6 6 FUEL LOADING GAL 7 SUB TOTAL RAMP CONDITION 8 LESS FUEL FOR START TAX1 AND TAKE OFF 9 SUB TOTAL TAKE OFF CONDLTION 10 LESS FUEL TO DESTINATION GAL 150 74 11 LANDING CONDITION 232 2 a Fuel for start taxi and take off is normally 5 lbs at an average mom 100 of 6 February 1979...

Page 134: ...02 o 150 156 158 168 213 216 O m c o m 160 166 168 179 227 230 U z m 170 177 179 190 241 245 Z 180 187 189 202 256 259 m 190 198 200 213 270 274 g 200 208 210 224 284 288 g 2 Q Effective M 1285 thru M 2006 z 01 a cm Effective M 2007 and after Ë Ë Reclining seat with back in full up position ye Values computed from a C G criterion based on a 170 pound male Differences in 2 o physical characteristic...

Page 135: ...cluded in Basic Empty Weight ARM 48 OTS WT MOMENT 100 8 15 7 USABLE FUEL ARM 117 GALLONS WEIGHT MOMENT 100 5 30 35 10 60 70 15 90 105 20 120 140 22 132 154 25 150 176 27 162 189 30 180 211 32 192 225 35 210 246 37 222 259 40 240 281 45 270 316 50 300 351 52 312 365 55 330 386 57 342 400 58 348 407 February 1979 6 19 ...

Page 136: ...er 180 Wtand Bal Equip List C23 M 1285and After USEFUL LOAD WEIGHTS AND MOMENTS BAGGAGE ARM 167 AñOMENT WEIGHT 100 10 17 20 33 30 50 40 67 50 84 60 100 70 117 80 134 90 150 100 167 110 184 120 200 130 217 140 234 6 20 February 1979 ...

Page 137: ...dals 7 5 Stabilator Trim System Manual Trim 7 6 Electric Trim 7 6 Instrument Panel 7 6 Switches 7 6 Illustration M 1285 thru M 1375 7 7 Illustration M 1376 thru M 1454 7 8 Illustration M 1455 thru M 1979 except M 1971 7 9 Illustration M 1971 M 1980 and after 7 10 Circuit Breakers 7 11 Flight Instruments 7 1 1 Ground Control 7 11 Wing Flaps Manual 7 12 Electric 7 12 Landing Gear 7 13 Brakes 7 13 Ja...

Page 138: ... 7 16 Engine 7 17 Engine Controls 7 17 Engine Instru ments 7 18 Vertical Readout Type 7 18 Dial Type 7 18 Exhaust Gas Temperature Indicator EGT 7 18 Engine Break in Information 7 18 Cowling 7 19 Lubrication System 7 19 Carburetor Heat 7 19 Starter 7 20 Propeller 7 20 Fuel System 7 20 Fuel Tanks 7 21 Fuel Drains 7 21 Fuel System Schematic 7 22 Fuel Quantity Indicators 7 21 Fuel Boost Pump 7 23 Engi...

Page 139: ...le 7 26 Lighting Systems Interior Lighting 7 28 Exterior Lighting 7 28 Environmental Systems Environmental Schematic 7 29 Cabin Heating 7 30 Ventilation 7 30 Exhaust Vent 7 31 Pitot and Static Systems Pitot System 7 31 Pitot Heat 7 31 Normal Static Air System 7 31 Emergency Static Air System 7 32 Vacuum System 7 32 Stall Warning System 7 32 January 1982 7 3 ...

Page 140: ...Section VII BEECHCRAFT Sundowner 180 Systems Description C23 M 1285 and After INTENTIONALLY LEFT BLANK 7 4 February 1979 ...

Page 141: ...the seat forward or aft as de sired Make certain the seat is locked securely in place after adjustment The backs of all individual seats can be placed in any of three positions Outboard armrests for the front seats are attached to the cabin doors FLIGHT CONTROLS CONTROL SURFACES The control surfaces are operated with conventional cable systems terminating in bellcranks CONTROL COLUMN A single cont...

Page 142: ...tion to operate the system The thumb switch is moved forward for nose down aft for nose up and when re leased returns to the center OFF position When the sys tem is not being electrically actuated the manual trim con trol wheel may be used INSTRUMENT PANEL The standard instrument panel consists of flight and navi gation instruments on the left and an avionics section on the right The switching pan...

Page 143: ...BEECHCRAFT Sundowner 180 Section VII C23 M 1285 and After Systerns Description o o o i oc I February 1979 7 7 ...

Page 144: ...Section VII BEECHCRAFT Sundowner 180 Systems Description C23 M 1285 and After u 7 8 February 1979 ...

Page 145: ...BEECHCRAFT Sundowner 180 Section VII C23 M 1285 and After Systems Description I O February 1979 7 9 ...

Page 146: ...Section VII BEECHCRAFT Sundowner 180 Systems Description C23 M 1285 and After o oog ees goe 7 10 February 1979 ...

Page 147: ...ach side of the fuselage just aft of the cabin M 1285 through M 1979 except M 1971 i instrument lights are turned on and dimmed by a rheostat switch located on the left subpanel and a rheostat switch located below the power quadrant M 1971 M 1980 and after Instrument lights are turned on and dimmed by two rheostat switches located on the pedestal below the power quadrant GROUND CONTROL Steering is...

Page 148: ... floor The thumb button does not need to be depressed nor should it be to lower the flaps ELECTRIC The electric wing flaps are controlled by a three position switch UP OFF and DOWN located to the right of the power quadrant The switch must be pulled out of detent before it can be repositioned A dial type indicator has markings for UP 10 DEGREES 20 DEGREES and DOWN The indicator is located adjacent...

Page 149: ... A hydraulic damper on the nose wheel strut compensates for any tendency to shimmy Toe brakes will aid in steering the airplane on the ground BRAKES The brakes on the main landing gear wheels are operated by applying toe pressure to the rudder pedals The parking brake push pull control is located on the right side of the lower left subpanel To set the parking brakes pull the con trol out and depre...

Page 150: ...t ment SEATS SEATBELTS ANDSHOULDERHARNESSES SEAT ADJUSTMENTS To adjust either of the front seats pull up on the release bar below the left hand seat corner and slide the seat forward or aft as desired Make certain the seat is locked securely in place after adjustment The backs of all individual seats can be placed in any of four positions Outboard armrests for the front seats are attached to the c...

Page 151: ...de wall structure at the aft edge of the respective seat The in ertia reel is covered with an escutcheon and the strap runs up from the reel to a looped fitting attached to the window frame just aft of the seat For stowing these shoulder harness straps stowage attach points are pro vided adjacent to the inertia reel on the cabin sidewall NOTE The seat belt is independent of the shoulder harness Ho...

Page 152: ...or from the inside lift the door release handle and pull until the door latch releases AFT BAGGAGE DOOR A baggage door aft of the cabin door on either the left or right side of the fuselage is provided for loading cargo into the aft cabin To open the door on the right side from the outside use the key provided to turn the cam lock To open the door on the left side from the outside grasp the flush ...

Page 153: ...d range is 1800 to 2700 rpm with a restricted operating range between 2150 and 2350 rpm for the 0 360 A2G engine only ENGINE CONTROLS The engine controls are centrally located for ease of opera tion from either the left or right seats The throttle on the power quadrant incorporates both a locking button and a vernier arrangement for fine adjustments The mixture control is locked with a clockwise t...

Page 154: ... the right fuel quantity indicator The tachometer and the fuel pressure indicator are located on the upper center of the instrument panel EXHAUST GAS TEMPERATURE INDICATOR EGT This installation provides for sensitive and rapid indica tion of exhaust gas temperature to assist in adjusting the fueVairmixture during cruise ENGINE BREAK IN INFORMATION New engines have been carefully run in by the engi...

Page 155: ...when operating temperatures are below normal and will permit the oil to bypass the cooler if it should become blocked CARBURETOR HEAT There is a possibility of ice forming in the induction sys tem under certain moist atmospheric conditions Gen erally ice may form in the vicinity of the carburetor butter fly and may build up enough that a drop in power output could result The induction installation...

Page 156: ...ever electrical power is being supplied to the starter Ifthe light remains illuminated after starting the starter relay has remained engaged and loss of electrical power and possible equipment damage will eventually result Turn the Battery Switch and Alternator Switch OFF If in flight land as soon as practical If the light does not illuminate during starting the indicator system is inoperative and...

Page 157: ...t must visually check the fuel level during preflight to ascertain desired level Fuel is fed from the desired tank through a fuel selector valve in the center floorboard and then through a strainer to the engine driven fuel pump FUEL DRAINS Two tank sump drains extend through the bottom of the wing skins near the fuselage M 1971 M 1980 and after have flush type drain valves The system low spot dra...

Page 158: ... FUEL PUMP CARBURETOR FIREWALL FITTINGS FIREWALL CHECK VALVE FUEL PRESSURE GAGE BOOST PUMP FUEL STRAINER AND DRAIN FUEL SELECTOR VALVE AND LEFT FUEL STRAINER HIGHT FUEL TANK TANK EFFECTIVE M 1820 M 1837 M 1842 M 1845 M 1853 M 1854 M 1856 M 1860 M 1861 M 1862 M 1865 M 1866 M 1869 M 1871 AND AFTER 7 22 February 1979 ...

Page 159: ... ject raw fuel into the induction system for cold starts After use secure the primer by turning it to lock it in the off position FUEL TANKSELECTION The fuel selector valve handle is located on the floorboards between the pilot and copilot seats Takeoffs and landings should be made using the tank that is more nearly full NOTE On serials M 2225 and after or on airplanes which have complied with BEE...

Page 160: ...ystem circuitry is the single wire ground return type with the airplane structure used as the ground return The battery alternator fuel boost and magneto start switches are located on the left subpanel The circuit breaker panel located on the right subpanel contains the protective circuit breakers for the various electrical systems Some switch type circuit breakers are located on the left subpanel...

Page 161: ...g dual switches are required to activate the circuit The switch placarded BATTERY ALT when placed in the ON position will only activate the battery circuit When this switch is on and the ALT FIELD switch is placed in the ON position the alternator is excited by power from the airplane battery When the BATTERY ALT switch is in the OFF position the alternator will be off regardless of the ALT FIELD ...

Page 162: ...n a fully charged condition Monitoring the am meter for proper operation of the alternator is the same as for a generator installation A zero reading which is nor mal in cruising flight indicates that the battery is fully charged and that the alternator output has been adjusted by the voltage regulator to balance the load of the electri cal equipment in use Should an alternator or regulator become...

Page 163: ...d directly tothe bat tery and continually energized Turn off battery and alternator switches and all electrical and avionics switches when connecting the auxiliary power unit plug Assure correct polarity negative ground before connecting auxiliary power unit Turn on the battery switch before turning on the auxiliary power unit On 28 volt airplanes a reverse polarity diode protection system is betw...

Page 164: ... for all of the exterior lights are located on the pilot s left subpanel Each circuit is protected by a circuit breaker switch circuit breaker or fuse The exterior lights consist of navigation lights on the wing tips and rudder a landing light on the left outboard wing and taxi lights on both outboard wings The landing light can be used for ap proach and taxiing For longer battery and lamp life us...

Page 165: ...FRESH AIR MIXER FRESH AIR INLET EXHAUST BOX DEFROST AIR AIR FIRE WALL FRESH AIR INLET C CLKE S 2 COCLKETIT ATER CABIN HEATER OUTLETS 3 FRESH AIR OUTLETS AFT CABIN BULKHEAD FIXED EXHAUST OPTIONAL VENTILATION FAN FRESH AIR INTAKE DORSAL FIN M 1875 M 1880 AND AFTER ENVIRONMENTAL SCHEMATIC February 1979 7 29 ...

Page 166: ...efrost Under extremely cold conditions heating in the back seats can be improved by partially pulling the defrost knob VENTILATION M 1285 thru M IS79 except M 1875 Fresh air for the cabin enters two grill type intakes im mediately forward of the windshield The air is ducted to four outlets one on either side of the instrument panel and to two overhead outlets for rear seat passengers The flow of a...

Page 167: ...d indicator The pitot mast is located on the leading edge of the left wing PITOT HEAT The pitot mast is provided with an electric heating ele ment which is turned on and off with a switch on the instrument panel The switch should be ON when flying in visible moisture It is not advisable to operate the pitot heating element on the ground except for testing or for short intervals of time to remove i...

Page 168: ...ge indicates system vacuum in inches of mer cury This instrument is located on the pilot s side of the instrument panel The vacuum should be maintained within the green arc for proper operation of the air driven instruments STALL WARNING SYSTEM A stall warning horn located in the overhead speaker con sole sounds a warning 5 to 7 mph above a stall condition and continues steadily as the airplane ap...

Page 169: ... Pilot 8 5 Alterations or Repairs to Airplane 8 5 Ground Handling 8 6 Towing 8 6 Parking 8 7 Control Column Lock Pin 8 7 Tie Down 8 7 Jacking 8 8 Flyable Storage 7 to 30 Days Mooring 8 8 Fuel Cells 8 9 Flight Control Surfaces 8 9 Grounding 8 9 Pitot Tube 8 9 Windshield and Windows 8 9 During Flyable Storage 8 9 Preparation for Service 8 10 Prolonged Out ofService Care 8 10 External Power Receptacl...

Page 170: ...8 17 AAinorFAaintenance Rubber Seals 8 17 Alternator 8 18 NAagnetos 8 18 Cleaning Exterior Painted Surfaces 8 19 Windshields and Windows 8 20 interior 8 21 Engine 8 22 Lubrication 8 22 Lubrication Points 8 23 Recommended Servicing Schedule 8 29 Consurnable Materials 8 34 Approved Engine Oils 8 36 Bulb Replacement Guide 8 38 Overhaul or Replacement Schedule 8 39 8 43 Inspections 8 43 Operational In...

Page 171: ... mechanics in conformity with all airworthiness requirements established for this airplane AII limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers and International Distributors or Dealers will have recommended modification service and operating procedures issued by ...

Page 172: ...re automatically provided to the holder of this manual For information on how to obtain Revision Service applicable to this manual consult any BEECHCRAFT Aero or Aviation Center or International Distributor or Dealer or refer to the latest revision of BEECH CRAFT Service Instructions No 0250 010 AIRPLANE INSPECTION PERIODS 1 FAA Required Annual Inspections 2 BEECHCRAFT Recommended inspection Guide...

Page 173: ...ventative maintenance 2 AII other maintenance must be performed by licensed personnel NOTE Pilots operating airplanes of other than U S registry should refer to the regulations of the registering authority for information con cerning preventative maintenance that may be performed by pilots ALTERATIONS OR REPAIRS TO AIRPLANE The FAA should be contacted prior to any alterations on the airplane to en...

Page 174: ...ity the nose gear steering yoke and or linkage may be damaged One person can move the airplane on a smooth and level surface using the hand tow bar furnished with the loose equipment Attach the tow bar to the tow lugs on the nose gear Idwer torque knee Where movement is restricted two people can pivot the airplane on the main wheels One person should push on the wing leading edge or hold the wing ...

Page 175: ...se or to exert excessive pressures CONTROL COLUMN LOCK PIN 1 Level the control wheel and move control column so the holes in the control column hanger and the control column will aÌignto accept the pin 2 Push the control column lock pin through the hole provided in the control column hanger and into the hole in the underside of the control column tube assembly 3 Ensure positive retention of the lo...

Page 176: ...e installed at the rear tie down lug and a tie down line attached to the nose gear JACKING Raise the individual gear for wheel and tire removal with a Iscissors jack under the axle Refer to the BEECHCRAFT Shop Manual for proper procedures DO NOT enter the airplane while the airplane is on a wheel jack FLYABLE STORAGE 7 TO 30 DAYS MOORING if the airplane cannot be placed in a hanger tie down secure...

Page 177: ...ND WINDOWS Close window vent DURING FLYABLESTORAGE In a favorable atmospheric environment the engine of an aircraft that is flown intermittently can be adequately pro tected from corrosion by turning the engine over five revolutions by means of the propeller This will dispel any beads of moisture that may have accummulated and spread the residual lubricating oil around the cylinder walls Unless th...

Page 178: ... the lower green arc range Ex cessive ground runup should be avoided PREPARAT ON FOR SERVICE Remove all covers clean the airplane and give it a thorough inspection particularly flaps and control openings Preflight the airplane PROLONGED OUT OF SERVICE CARE The storage procedures listed are intended to protect the airplane from deterioration while it is not in use The pri mary objectives of these m...

Page 179: ...efore connecting auxiliary power unit Turn on the battery switch before turning on the auxiliary power unit On 28 volt airplanes a reverse polarity diode protection system is between the external power receptacle and the main bus With external power applied the bus is powered Turn on the battery switch only with all other switches including avionics switches off when connecting the auxiliary power...

Page 180: ...ws an increase in the payload The fuel indicators on the instrument panel will indicate full tanks even though each tank contains only 20 gallons of fuel CAUTION Connect a grounding cable from the fuel ser vice unit to the airframe and connect ground ing cables from both the fuel service unit and the airplane to ground during fueling opera tions This procedure reduces fire hazard FUEL DRAINS Open ...

Page 181: ...requency will depend upon service conditions and fuel handling cleanliness When operating in localities where there is an excessive amount of sand or dirt the strainers should be inspected at more frequent intervals The screen in the fuel strainer at the system low spot on the bottom of the fuselage should be removed and washed in fresh cleaning solvent at each 100 hour inspection of the airplane ...

Page 182: ...ht quarts The normal operating range is six to eight quarts BATTERY 14 VOLT SYSTEM A 12 volt 25 amp hour lead acid battery located directly aft of the cabin area may be reached by removing the rear panel 28 VOLT SYSTEM One 24 volt 15 5 amp hour lead acid battery or two 12 volt 25 amp hour lead acid batteries connected in series are located directly aft of the cabin area and may be reached by remov...

Page 183: ...lane is equipped with tube type tires Inflate the 17 50 x 6 00 x 6 main or nose gear tires to 22 psi and the 15 x 6 00 x 6 main or nose gear tires to 40 psi Maintain ing proper tire inflation will minimize tread wear and aid in preventing tire failure caused from running over sharp stones When inflating tires visually inspect them for cracks and breaks CAUTION I Beech Aircraft Corporation cannot r...

Page 184: ...it INDUCTION AIR FILTER This filter should be inspected for foreign matter at least once during each 50 hour operating period In adverse climatic conditions or if the airplane is stored preflight inspection is recommended To remove and clean the filter 1 Remove the filter retaining screws 2 Remove the filter 3 Clean and service as described in the manufacturer s instructions on the filter 4 Reinst...

Page 185: ...icular attention It is very important that all nicks and scratches be smoothed out and polished The BEECHCRAFT Aero or Aviation Center and International Distributors or Dealers will be glad to answer any questions concerning propeller blade repair WARNING When servicing a propeller always make certain the ignition switch is off and that the engine has cooled completely WHEN MOVING A PROPELLER STAN...

Page 186: ... the negative battery terminals together and the positive battery terminals together 3 When using a battery charger connect the positive lead of the charger to the positive battery terminal and the negative lead of the charger to the negative battery terminal 4 Do not operate an alternator on open circuit Be sure all circuit connections are secure 5 Do not short across or ground any of the termina...

Page 187: ...f the magneto should be removed CLEANING EXTERIOR PAINTED SURFACES CAUTION Do not apply wax or polish for a paint cure period of 90 days after delivery Waxes and polishes seal the paint from the air and prevent curing Wash uncured painted surfaces with cold or lukewarm water and a MILD NON DETERGENT SOAP Any rubbing of the surface should be done gently and held to a minimum to avoid cracking the p...

Page 188: ...hing with solvent lubricate all lubrication points Premature wear of lubricated surfaces may result if the above precautions are not taken WINDSHIELD AND WINDOWS The windshield and plastic windows should be kept clean and waxed at all times To prevent scratches wash the windows carefully with plenty of soap and water using the palm of the hand to feel and dislodge dirt and mud A soft cloth chamois...

Page 189: ...hold it for several seconds Continue blotting until no more liquid 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 instruc tions on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it ma...

Page 190: ... the airplane components in top condition If this operation is per formed thoroughly general maintenance will be reduced and the service life of the airplane will be greatly increased The grease fittings or parts must be wiped clean to make sure that no dirt is carried into the part when lubricated Apply lubricant sparingly but with assurance that the bearing surfaces are adequately covered Wipe o...

Page 191: ...BEECHCRAFT Sundowner 180 Section VIII C23 M 1285 and After Handling Serv Maint LUBRICATION POINTS D C F E H L A DETAIL A NOSE GEAR STEERING February 1979 8 23 ...

Page 192: ...Section VIII BEECHCRAFT Sundowner 180 Handling Serv Maint C23 M 1285 and After DETAIL B 11 FLAP MECHANISM DETAIL C RUDDER BELLCRANK DETAIL D RUDDER HINGE 8 24 February 1979 ...

Page 193: ...AFT Sundowner 180 Section VIII C23 M 1285and After Handling Serv Maint DETAIL E OR ELEVATOR HINGE DETAIL F DETAIL G O á o STABILATOR HINGE AILERON BELLCRANK BRACKET DETAIL H 11 RUDDER PEDALS February 1979 8 25 ...

Page 194: ...Section VIII BEECHCRAFT Sundowner 180 Handling Serv Maint C23 M 1285 and After DETAIL I LANDING GEAR DETAIL J CONTROL COLUMN LINKAGE DETAIL K TRIM TAB ACTUATOR 8 26 February 1979 ...

Page 195: ...tely tight to prevent binding LOOSEN NUT REMOVE VALVE CONE AND LUBRICATE CONE WITH VERY THIN COATING OF LUBRICANT NOTE DO NOT OVER LUBRICATE VALVE CONE APPLY MINIMUM AMOUNT OF LUBRICANT FOR COATING FUEL SELECTOR VALVE NOTE FUEL SELECTOR VALVES ON M 1486 AND AFTER NEED NO LUBRICATION DETAIL M I m oá AILERON HINGE AND ROD ENDS February 1979 8 27 ...

Page 196: ...NOTE Numbers refer to items in the consumable materials chart Lubricate all plain bearing bushings as required or every 500 hours with SAE No 30 oli Apply SAE No 20 oil to push pull control housings as required Lubricate flight control pully bushings with SAE No 30 oil every 1000 hours SAE 10w 30 oil is an acceptable replacement for SAE 20 or SAE 30 oil 8 28 February 1979 ...

Page 197: ...Drain fuel tank drains Inboard bottom of wings Drain fuel system low spot Bottom of fuselage Service fuel tanks Top of wings 3 m 25 Hrs Check battery electrolyte Behind aft cabin bulkhead See Maintenance Manual Clean induction air filter In lower forward cowl Lubricate landing gear On landing gear I 5 knee pins 50 Hrs Change engine oil Lower side of engine 1 Clean oil screens Aft right side of acc...

Page 198: ...ewall screen m Lubricate wheel bearings Landing gear 1 8 Lubricate nose gear rod On top of nose gear A 11 end bearings Lubricate nose gear swivel On aft side of nose gear A 5 Lubricate flap torque tubes Under floorboards B 14 Lubricate flap rod end Inboard end of flaps B 11 bearings Lubricate rudder bellcrank Bottom of rudder C 11 pivot points Ë Lubricate rudder hinges On rudder leading edge D 11 ...

Page 199: ...od ends wings M 300 Hrs Replace induction air filter In front nose cowl go 500 Hrs Lubricate rudder pedal Forward cabin floor H 11 bellcrank Lubricate rudder pedal Forward cabin floor H 11 rod ends Replace gyro instrument Behind instrument panel central filter 1000 Hrs Lubricate control column Behind instrument panel J 11 oo pivot points go 1200 Hrs Lubricate trim tab actuator In aft tail section ...

Page 200: ...o Lubrication to item on INTERVAL ITEM Points Diagram Consumable Materials As Req Fuel selector valve Center floorboard L 15 Central brake reservoir On firewall N 7 Clean spark plugs In engine compartment m Note 3 Replace Emergency Right side of aft fuselage Locator Transmitter Battery ...

Page 201: ...bolts for proper torque at the first 100 hour inspection and at the N 2 first 100 hour inspection after each reinstallation of the wing attach bolts o 3 Rechargeable Batteries Recharge after one cumulative hour of use or after 50 of the useful charge life Non rechargeable Batteries Replace after one cumulative hour or as noted on the o battery ...

Page 202: ...91 96 blue 100 green or 100LL blue Grade I 4 Molybdenum MIL M 7866 Disulfide 5 Grease High Aero Lubriplate Low Tempera ture 6 Corrosion Preven MIL C 6529 tive Engine 7 Hydraulic Fluid MIL H 5606 8 Grease General MIL G 81322 Purpose Wide Temperature 9 Grease High MIL G 23827 Low Tempera ture 10 Lubricating Oil MIL L 7870 Low Tempera ture 1 1 Lubricating Oil SAE No 20 or 10W 30 12 Lubricating Oil SA...

Page 203: ...r 301 E approved for use lubricating oils which conform to both MIL L 6082B straight mineral type and MIL L 22851 ashless dispersant lubricants for airplane engines If grade 91 96 blue fuel is not available use 100 green or 100LL blue I Mix with naphtha into paste and apply with a brush Product of Alcor Inc San Antonio Texas 78284 Product of BRC Bearing Company Wichita Kansas ln extremely cold cli...

Page 204: ... A Code 60068 Aeroshell W120 Aeroshell W80 Texaco Incorporated TX 6309 Aircraft Engine Oil Premium AD120 Aircraft Engine Oil Premium AD80 American Oil and PQ Aviation Lubricant 753 Supply Co Chevron Oil Company Chevron Aero Oil Grade 120 Humble Oil and Esso Aviation Oil E 120 Refining Co Enco Aviation Oil E 120 Esso Aviation Oil A 100 Enco Aviation Oil A 100 Esso Aviation Oil E 80 Enco Aviation Oi...

Page 205: ...l 1065 Company Conoco Aero Oil 1100 Mobil Oil Corporation Avrex 101 1065 101 1100 Phillips Petroleum Co Phillips 66 Aviation Engine Oil Grade 1065 Phillips 66 Aviation Engine Oil Grade 1100 Shell Oil Company Aeroshell Oil 65 Aeroshell Oil 100 Ashless Dispersant Oils Complying with MIL L 22851 NOTE Ashless dispersant oil complying with MIL L 22851 is recommended after the oil consump tion has stabi...

Page 206: ...endors listed as meeting Federal and Military Specifica tions are provided as reference only and are not specifi cally recommended by Beech Aircraft Corporation Any product conforming to the specification may be used BULB REPLACEMENT GUIDE LOCATION NUMBER 14 VOLT 28 VOLT Compass light 330 327 Dome light cabin 89 303 Instrument flood light 89 303 overhead Landing light wing 4313 4596 Navigation lig...

Page 207: ...noted in this handbook are based on average usage and average environmental conditions SPECIAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion and or lack of lubrication In these areas periodic inspections should be performed until ...

Page 208: ...els and Tires On Condition POWER PLANT NOTE When an engine has been overhauled or a new engine installed it is recommended that low power settings NOT be used until oil con sumption has stabilized The average time for piston ring seating is approximately 50 hours Refer to Lycoming Engine Operator s Manual Engine O 360 A2G 2000 hours O 360 A4G 2000 hours O 360 A4J 2000 hours O 360 A4K 2000 hours En...

Page 209: ...t Muffler Shroud Inspect every 100 hours All Hose carrying At engine overhaul or every flammable liquid 5 years All other hoses on condition Vacuum System Filter Every 300 Hours Vacuum Regulator Valve On Condition Vacuum Pump At engine overhaul or on condition K FUEL SYSTEM Fuel Boost Pump On condition All Hose carrying At engine overhaul or flammable liquid every 5 years AII Hose not carrying On ...

Page 210: ...te of Climb indicator On Condition Fuel Quantity Indicator On Condition Fuel Pressure Indicator On Condition Tachometer On Condition Free Air Temperature On Condition Indicator Flap Position Indicator On Condition ELECTRICAL SYSTEM Battery Master Relay On Condition All other Relays On Condition Voltage Regulator On Condition Starter Relay On Condition FIAPS AND FLIGHT CONTROLS Flight Controls On C...

Page 211: ...el on an annual basis Good operating practice requires that the airplane be pre flighted prior to takeoff Items found during preflight and engine run up should be corrected on the basis of their im portanée to the safe operation of the airplane however in any event early correction of items found is good pre ventative maintenance Although it is not a requirement that FAA qualified per sonnel chang...

Page 212: ...lectrical switches and circuit breakers 14 Power check 2250 to 2350 rpm static Power Plant 1 Oil screens cleaned 2 Induction air filter cleaned 3 Check engine controls wiring harness and plumbing for clearance and security 4 Check propeller for rock damage and spinner and spinner bulkheads for cracks and security engine for oil leaks 5 Check engine baffles and cowling for cracks and security 6 Che...

Page 213: ...ction of travel 2 Storm window and door operation 3 Check interior furnishings and seat belts 4 Check battery water level Exterior 1 Check flight control surfaces for condition and security 2 Check tires brake pucks and discs 3 Check static ports pitot mast and fuel vent lines for obstructions 4 Check general condition of fuselage and wings February 1979 8 45 ...

Page 214: ...Section VIII BEECHCRAFT Sundowner 180 Handling Serv Maint C23 M 1 285 and After INTENTIONALLY LEFT BLANK 8 46 February 1979 ...

Page 215: ... was installed or not Supplements for equipment for which the vendor obtained a Supplemental Type Certificate were included as loose equipment with the airplane at the time of delivery These and other Supplements for other equipment that was installed after the airplane was delivered new from the factory should be placed in this SUPPLEMENTS Section of this Pilot s Operating Handbook and FAA Approv...

Page 216: ...Section IX BEECHCRAFT Sundowner 180 Supplements C23 M 1285 and After INTENTIONALLY LEFT BLANK 9 2 February 1979 ...

Page 217: ...A APPROVED AIRPLANE FLIGHT MANUAL LOG OF SUPPLEMENTS FAA Supplements must be in the airplane for flight operation whe n subject equiptrent is installed Supp Part Rev No Number Subject No Date 1 169 590008 9 Acrobatic 2 79 2 169 590008 19 Single Door 2 79 3 MCO C32644 11 Static Air 6 78 February 1979 9 3 ...

Page 218: ...Section IX BEECHCRAFT Sundowner 180 Supplements C23 M 1285 and After INTENTIONALLY LEFT BLANK 9 4 February 1979 ...

Page 219: ...The maneuver is entered at 140 MPH 122 KTS lAS at 2700 RPM A 3 0 to 3 5 G pull up is recommended The airspeed at the top of the loop will be 50 to 60 MPH 43 to 52 KTS IAS which is fast enough to retain positive acceleration and prevent a stall Completion of the loop is accomplished by keeping the G Ievel just below that where a buffet occurs The altitude loss is 50 to 100 feet IMMELMANN The maneuv...

Page 220: ...altitude loss will be 800 feet The throttle is to be retarded as the nose drops past the horizon in the inverted position WARNING Do not use abrupt or full control travel at speeds greater than the maximum design maneuvering speed Spins are approved Spins have not been demonstrated in excess of 6 turns For spin entry and recovery see pages 3 10 and 3 11 of this Pilot s Operating Handbook and FAA A...

Page 221: ... modified with a single entrance door which has been installed in accordance with BEECH CRAFT FAA approved data This document supersedes or adds to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only where covered in the items contained herein LIMITATIONS No change EMERGENCY PROCEDURES No change NORMAL PROCEDURES PREFLIGHT INSPECTION 1 CAB N a Parking Brake SET b Control Lo...

Page 222: ...UNOBSTRUCTED c Aileron CHECK d Wing Tip CHECK e Position Light CHECK 6 LEFT WINGLEADING EDGE a Pitot Tube CHECK Remove Cover b Landing Light CHECK c Tie Down and Chocks REMOVE d Stall Warning CHECK for movement of vane e Fuel Tank CHECK O UANTITY Filler Cap SECURE 7 LEFT LANDINGGEAR a Tire and Nose Gear CHECK b Fuel Sump DRAIN 8 NOSE SECTION a Left Cowl SECURE b Induction Air Intake CLEAR c Propel...

Page 223: ...el Sump DRAIN b Tire and Brake CHECK 10 R GHT W NG LEADING EDGE a Fuel Tank CHECK QUANTITY Filler Cap SECURE b Tie Down and Chocks REMOVE c Wing Tip CHECK d Position Light CHECK 11 R GHT WlNG TRA L NG EDGE a Aileron CHECK b Flap CHECK c Fuel Tank Vent Line UNOBSTRUCTED 8 6 7 9 mumml O 4 2 3 FAA Approved Revised February 1979 P N 169 590008 19 3 of 4 ...

Page 224: ...PERFORMANCE No change Approved W H Schultz Beech Aircraft Corporation DOA CE 2 FAA Approved Revised February 1979 4 of 4 P N 169 590008 19 ...

Page 225: ...lane when modified by the installation of the Beechcraft Emergency Static Air Source LIMITATIONS PLACARDS o WARNING e EMERGENCY AIRSPEED STATIC SOURCE ON SEE P1LOTSCHECK LI T EMERGENC OR FLIGHT MANUAL EMERGENCYPROCEDURES FOR AIRSPEED ALTIMETER OFF CALIBRATION ERROR NORMAL Or o WARNING o EMERGENCY AIRSPEED STATICSOURCE EMERGENCY r ON SEE PILOTS CHECK LIST OR FLIGHT MANUAL OFF EMERGENCY PROCEDURES F...

Page 226: ...desired for use 1 Pilot s Emergency Static Air Source Switch to ON EMERGENCY lower sidewall adjacent to pilot 2 For airspeed calibration and altimeter correction refer to AIRSPEED CALIBRATION EMERGENCY SYSTEM and ALTIMETER CORRECTION EMERGENCY SYSTEM graphs in the PERFORMANCE section CAUTION Be certain the emergency static airvalve is in the OFF NORMAL position when system is not needed NORMAL PRO...

Page 227: ...150 130 140 120 140 120 130 110 120 130 110 110 100 i 120 90 e 110 100 90 90 80 100 90_ 80 80 70 80 70 70 60 70 60 60 50 63 73 E3 93 1 0 1 0 1 0 1 0 1iO 1 0 Tr0 1 0 1 0 190 2 0 f 0 60 7 80 9 14 1 0 1 0 lAS IN ICA ED AIRSP ED KNOTS I 1S INDit ATED AIRSPEE ENOT lilllllllllllllli llilllll 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 60 70 80 90 100 110 120 130 140 IAS INDICATED AI...

Page 228: ...FT MENT ERROR O O 10 10 20 FLAPS UP 0 I 20 FLAPS DOWN 35 2 30 30 40 40 50 50 OO 60 oo 60 70 70 90 90 60 70 80 90 100 110 120 130 140 150 160 110 50 60 70 80 90 100 110 IAS INDICATED AIRSPEED KNOTS lAS INDICATED AIRSPEED KNOTS I I I I I I I 1 I I I I I I I I I I I I I I 70 80 90 100 110 120 130 140 150 160 170 180 190 200 60 70 80 90 100 110 120 130 IAS INDICATED AIRSPEED MPH IAS INDICATED AIRSPEED...

Page 229: ...mb or descent Verification of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of climb This may be accompanied by abnormal indicated airspeed and altitudechanges beyond normal calibration differences HANDLING SERVICING AND MAINTENANCE EMERGENCY STATICAIR SOURCE The system should be drained every 100 hours Remove cover plate from t...

Page 230: ......

Page 231: ...irman s Information Manual 10 11 Airman s Information Manual 10 11 Advisory Information 10 13 FAA Advisory Circulars 10 13 FAA General Aviation News 10 18 FAA Accident Prevention Program 10 19 GENERAL INFORMATION ON SPECIFIC TOPICS 10 20 Flight Planning 10 20 Passenger Information Cards 10 21 Inspections Maintenance 10 22 Flight Operations 10 22 General 10 22 Turbulent Weather 10 22 Flight in Icin...

Page 232: ... of Climb Speed Vyse 10 42 Best Single Engine Angle of Climb Airspeed V xse 10 43 Single Engine Service Ceiling 10 44 Basic Single Engine Procedures 10 44 Engine Failure on Take Off 10 45 When to fly Vx Vy Vxse and Vyse 10 46 Stalls Slow Flight and Training 10 47 Spins 10 50 Descent l0 55 Vortices Wake Turbulence 10 56 Takeoff and Landing Conditions 10 57 Medical Facts for Pilots 10 58 General 10 ...

Page 233: ...BEECHCRAFT Section X Safety Information TABLE OF CONTENTS Cont d ADDITIONAL INFORMATION 10 64 Special Conditions 10 66 Maintenance 10 66 March 1981 10 3 ...

Page 234: ...e or more of the following placards Owners Manual FAA Flight Manual Pilots Operating Handbook and FAA Approved Flight Manual For simplicity and convenience we will refer to all official manuals in various models as the Information Manual If the airplane has changed ownership the Information Manual may have been misplaced or may not be current If missing or out of date replacement Information Manua...

Page 235: ...d built to provide owners and pilots with many years of safe and efficient transportation By maintaining it properly and flying it prudently you will realize its full potential WARNING Because your aircraft is a high performance high speed transportation vehicle designed for operation in a three dimensional environment special safety precautions must be observed to reduce the risk of fatal or seri...

Page 236: ...properly licensed and rated and thoroughly familiar with the contents of the Information Manual to operate the aircraft IMPROPER OPERATION OR MAINTENANCE OF AN AIRCRAFT NO MATTER HOW WELL BUILT INITIALLY CAN RESULT IN CONSIDERABLE DAMAGE OR TOTAL DESTRUCTION OF THE AIRCRAFT ALONG WITH SERIOUS OR FATAL INJURIES TO ALL OCCUPANTS BEECH AIRCRAFT CORPORATION 10 6 March 1981 ...

Page 237: ...s in limited detail Here are some condensed Do s and Don ts DO S Be thoroughly familiar with your airplane know its limitations and your own Be current in your airplane or fly with a qualified instructor until you are current proficient Pre plan all aspects of your flight including weather and adequate fuel reserves Use services available Weather briefing in flight weather and Flight Service Stati...

Page 238: ...rols during pre flight inspection and before takeoff Maintain the prescribed airspeeds in takeoff climb descent and landing Avoid big airplane wake turbulence Preplan fuel and fuel tank management before the actual flight Utilize auxiliary tanks only in level cruise flight Take off and land on the fullest main tank Practice emergency procedures at safe altitudes and airspeeds preferably with a qua...

Page 239: ...in a reckless show off careless manner Don t fly into thunderstorms or severe weather Don t fly in possible icing conditions unless the airplane is approved and properly equipped Don t fly close to mountainous terrain Don t apply controls abruptly or with high forces that could exceed design loads of the airplane Don t fly into weather conditions that are beyond your ratings or current proficiency...

Page 240: ...nd be prepared for an emergency in the remote event that one should occur You as a pilot have responsibilities under government regulations These are designed for your protection and the protection of your passengers Compliance is mandatory RULES AND REGULATIONS F A R Part 91 General Operating and Flight Rules is a document of law governing operation of aircraft and the owner s and pilot s respons...

Page 241: ... pilot s responsibility to be thoroughly familiar with all items in F A R Part 91 and to follow them AIRWORTHINESS DIRECTIVES F A R Part 39 specifies that no person may operate a product to which an airworthiness directive issued by the FAA applies except in accordance with the requirements of that airworthiness directive AIRMAN INFORMATION ADVISORIES AND NOTICES FAA A RMAN S INFORMATION MANUAL AI...

Page 242: ...ormation on safety and accident and hazard reporting It is revised at six month intervals and can be purchased locally or from the Superintendent of Documents U S Government Printing Office Washington D C 20402 This document contains a wealth of pilot information Among the subjects are Controlled Air Space Services Available to Pilots Radio Phraseology and Technique Airport Operations Clearances a...

Page 243: ...mple an airport closed terminal radar out of service enroute navigational aids out of service etc Airmen can subscribe to services to obtain FAA NOTAMS and Airman Advisories and these are also available at FAA Flight Service Stations FAA ADVISORY CIRCULARS The FAA issues advisory circulars to inform the aviation public in a systematic way of non regulatory material of interest Advisory Circulars c...

Page 244: ...t to pilots are 00 6A Aviation Weather 00 24 Thunderstorms 00 30 Rules of Thumb for Avoiding or Minimizing Encounters with Clear Air Turbulence 00 45A Aviation Weather Services 00 46A Aviation Safety Reporting Program 00 50 Low Level Wind Shear 20 5D Plane Sense 20 93 Flutter Due to Ice or Foreign Substance on or in Aircraft Control Surfaces 20 105 Engine Power Loss Accident Prevention 39 7 Airwor...

Page 245: ...ment Rating Written Test Guide 61 9B Pilot Transition Courses for Complex Single Engine and Light Twin Engine Airplanes 61 10A Private and Commercial Pilots Refresher Courses 61 12J Student Pilot Guide 61 19 Safety Hazard Associated with Simulated Instrument Flights 61 21 Flight Training Handbook 61 23A Pilot s Handbook of Aeronautical Knowledge 61 27B Instrument Flying Handbook 61 32B Private Pil...

Page 246: ...art 61 Revised Certification Pilot and Flight Instructors 61 67 Hazards Associated with Spins in Airplanes Prohibited from Intentional Spinning 61 70 Flight Instructor Instrument Airplane Written Test Guide 6I 71A Commercial Pilot Airplane Written Test Guide 61 72A Flight Instructor Airplane Written Test Guide 61 84 Role of Preflight Preparation 67 2 Medical Handbook for Pilots 90 23D Wake Turbule...

Page 247: ...rns for Airplane Operations at Uncontrolled Airports 91 6A Water Slush and Snow on runway 91 8A Use of Oxygen by General Aviation Pilots Passengers 91 llB Annual Inspection Reminder 91 13C Cold Weather Operation of Aircraft 91 17 The use of View Limiting Devices on Aircraft 91 23A Pilot s Weight and Balance Handbook 91 24 Aircraft Hydroplaning or Aquaplaning on Wet Runways 91 25A Loss of Visual Cu...

Page 248: ...n Dioxide Dry Ice Aboard Aircraft 150 5200 3A Bird Hazards to Aircraft 210 1A National Notice to Airmen System 210 5 Military Flying Activities Advisory Circulars that are for sale FAA GENERAL AVIATION NEWS FAA General Aviation News is published by the FAA in the interest of flight safety The magazine is designed to promote safety in the air by calling the attention of general aviation airmen to c...

Page 249: ...onducts seminars and workshops and distributes invaluable safety information under this program Usually the airport manager the FAA Flight Service Stations FSS or Fixed Base Operator F B O will have a list of accident prevention counselors and their phone numbers available All Flight Standards and General Aviation District Offices have a list of the counselors serving the district Before flying ov...

Page 250: ...al enroute and destination weather and enroute navaid information Enroute terrain and obstructions alternate airports airport runways active length of runways and take off and landing distances for the airplane for conditions expected should be known The prudent pilot will review his planned enroute track and stations and make a list for quick reference It is strongly recommended a flight plan be ...

Page 251: ...roduction airplanes passenger information cards which contain important information on the proper use of restraint systems oxygen masks emergency exits and emergency bracing procedures Passenger information cards may be obtained at any Beechcraft Aviation or Aero Center A pilot should not only be familiar with the information contained in the cards himself but should prior to flight always inform ...

Page 252: ...n and that proper maintenance records are kept Each airplane has a checklist for the pre flight inspection which must be followed USE THE CHECKLIST FLIGHT OPERATIONS GENERAL The pilot must be thoroughly familiar with all information published by the manufacturer concerning the airplane and is required by law to operate the airplane in accordance with the FAA Approved Airplane Flight Manual and or ...

Page 253: ...s Thunderstorms squall lines and violent turbulence should be regarded as extremely dangerous and must be avoided Hail and tornadic wind velocities can be encountered in thunderstorms that can destroy any airplane just as tornadoes destroy nearly everything in their path on the ground Turboprop Engines Thunderstorms also pose the possibility of a lightning strike on an aircraft Any structure or eq...

Page 254: ...d flight in turbulent air may be encountered unexpectedly under certain conditions The following recommendations should be observed for airplane operation in turbulent air Flying through turbulent air presents two basic problems the answer to both of which is proper airspeed On one hand if you maintain an excessive airspeed you run the risk of structural damage or failure on the other hand if your...

Page 255: ...g forward or back pressure to keep the nose level Maintain straight and level attitude in either up or down drafts Use trim sparingly to avoid being grossly out of trim as the vertical air columns change velocity and direction If necessary to avoid excessive airspeeds lower the landing gear FLIGHT IN IC NG CONDITIONS Every pilot of Beech airplanes for that matter the pilot of any airplane should b...

Page 256: ...of deicing anti icing equipment removes prevents accumulation It does not present a problem if the deicing anti icing equipment is used Moderate The rate of accumulation is such that even short encounters become potentially hazardous and use of deicinglanti icing equipment or diversion is necessary Severe The rate of accumulation is such that deicinglanti icing equipment fails to reduce or control...

Page 257: ...t in icing conditions and plan the flight accordingly if icing conditions are known or forecast along the route Every owner and pilot of an airplane should understand that it is not uncommon to find aircraft equipped with less than the full complement of available systems and equipment For example props and pitot tube may be protected but the aircraft might not have wing boots or tail boots The re...

Page 258: ...mediate diversion by flying out of the area of visible moisture or going to an altitude where icing is not encountered Some models of Beech airplanes were approved for flight in certain limited icing conditions under the FAA s Bureau of Flight Standards Release No 434 Under this release properly equipped airplanes are approved for flight in light to moderate icing conditions only These aircraft ar...

Page 259: ... tornados hurricanes or other phenomena likely to produce severe turbulence airplanes equipped for flight in icing conditions cannot be expected to cope with severe icing conditions as defined by the National Weather Service The prudent pilot must remain alert to the possiblity that icing conditions may become severe and that his equipment will not cope with them At the first indication that such ...

Page 260: ... of the area protected by the boots The fact or extent of ice buihi up in unprotected areas will not be directly observable from the cockpit Due to distortion of the wing airfoil increased drag and reduced lift stalling speeds will increase as ice accumulates on the airplane For the same reasons stall warning devices are not accurate and cannot be relied upon in icing conditions Even though the pi...

Page 261: ... operating even a fully equipped airplane in sustained icing conditions must remain sensitive to any indication such as observed ice accumulation loss of airspeed the need for increased power reduced rate of climb or sluggish response that ice is accumulating on unprotected surfaces and that continued flight in these conditions is éxtremely hazardous regardless of the performance of the deicing an...

Page 262: ...important ingredients to safe flight in icing conditions regardless of the aircraft or the combination of deicinglanti icing equipment are a complete and current weather briefing sound pilot judgment close attention to the rate and type of ice accumulations and the knowledge that severe icing as defined by the National Weather Service is beyond the capability of modern aircraft and immediate diver...

Page 263: ...fects of topographic features on weather conditions Many good articles have been published and a synopsis of mountain flying operations is included in the FAA Airman s Information Manual Part 1 Avoid flight at low altitudes over mountainous terrain particularly near the lee slopes If the wind velocity near the level of the ridge is in excess of 25 knots and approximately perpendicular to the ridge...

Page 264: ...aft may exceed the climb capability of your airplane Avoid mountain wave downdrafts VFR LOW CE L NGS If you are not instrument rated do not attempt VFR on Top or Special VFR flight or clearances Being caught above a solid cloud layer when an emergency descent is required or at destination is an extremely hazardous position for the VFR pilot Accepting a clearance out of certain airport control zone...

Page 265: ...ime to miss them Flight on dark nights over sparsely populated country can be the same as IFR and must be avoided by inexperienced or non IFR rated pilots VERTIGO DISORIENTATION Disorientation can occur in a variety of ways During flight inner ear balancing mechanisms are subjected to varied forces not normally experienced on the ground This combined with loss of outside visual reference can cause...

Page 266: ...ning flights The VFR pilot should use extra caution in avoiding low visibility conditions Motion sickness often precedes or accompanies disorientation and may further jeopardize the flight Disorientation in low visibility conditions is not limited to VFR pilots Although IFR pilots are trained to look at their instruments to gain an artificial visual reference as a replacement for the loss of a vis...

Page 267: ... control is sustained it will result in an excessive speed accident Excessive speed accidents occur in one of two manners either as an inflight airframe separation or as a high speed ground impact and they are fatal accidents in either case All airplanes are subject to this form of accident For years Beech Information Manuals have contained instructions that the landing gear should be extended in ...

Page 268: ...elow a certain speed maximum maneuvering speed As a result the control surfaces should never be suddenly or fully deflected above maximum maneuvering speed Turbulence penetration should not be performed above that speed The accidents we are discussing here occur at airspeeds greatly in excess of these limitations No airplane should ever be flown beyond its FAA approved operating limitations FL GHT...

Page 269: ...iously represents a 50 loss of horsepower but in virtually all light twins climb performance is reduced by at least 80 A study of the charts in your Information Manual will confirm this fact Single engine climb performance depends on four factors Airspeed too little or too much will decrease climb performance Drag gear flaps cowl flaps prop and speed Power amount available in excess of that needed...

Page 270: ...be balanced by banking slightly up to 5 into the operating engine Airspeed is the key to safe single engine operations For most light twins there is an Symbol airspeed below which directional control cannot be maintained Vmca airspeed below which an intentional engine cut should never be made Vsse airspeed that will give the best single engine rate of climb or the slowest loss of altitude Vyse air...

Page 271: ...eading change and thereafter maintain straight flight with not more than 5 degrees of bank if one engine fails suddenly with Take off power on both engines Rearmost allowable center of gravity Flaps in takeoff position Landing gear retracted Propeller windmilling in takeoff pitch configuration or feathered if automatically featherable However sudden engine failures rarely occur with all of the fac...

Page 272: ...ure NTENTIONAL ONE ENGINE NOPERAT VESPEED Vsse Vsse is specified by the airplane manufacturer and is the minimum speed at which to perform intentional engine cuts Use of Vsse is intended to reduce the accident potential from loss of control after engine cuts at or near minimum control speed Vmca demonstrations are necessary in training but should only be made at a safe altitude above the terrain a...

Page 273: ...e Drag caused by a windmilling propeller extending landing gear or flaps in the landing position will severely degrade or destroy single engine climb performance Since engine climb performance varies widely with type of airplane weight temperature altitude and airplane configuration the climb gradient altitude gain or loss per mile may be marginal or even negative under some conditions Study the I...

Page 274: ...g chart should be used during flight planning to determine whether the airplane as loaded can maintain the Minimum Enroute Altitude MEA if IFR or terrain clearance if VFR following an engine failure BASIC SINGLE ENGINE PROCEDURES Know and follow to the letter the single engine emergency procedures specified in your Information Manual for your specific make and model airplane However the basic fund...

Page 275: ...to be sure that the inoperative engine is secured properly and that the appropriate switches are placed in the correct position The airplane must be banked about 5 into the live engine with the slip skid ball out of center toward the live engine to achieve rated performance Another note of caution Be sure to identify the dead engine positively before feathering it Remember First identify the suspe...

Page 276: ...g the runway length required to stop if the engine fails before reaching lift off speed and also has charts showing single engine performance after lift off Study your charts carefully No airplane is capable of climbing out on one engine under all weight pressure altitude and temperature conditions Know before you take the actual runway whether you can maintain control and climb out if you lose an...

Page 277: ...m must be kept operational at all times and must not be deactivated by interruption of circuits circuit breakers or fuses Compliance with this requirement is especially important in all high performance single and multi engine airplanes during engine out practice or stall demonstrations because the stall speed is critical in all low speed operations of high performance airplanes Training should be...

Page 278: ...ver been required by the FAA regulations for multi engine flight tests and should not be practiced in high performance airplanes by other than qualified engineering test pilots Engine out minimum control speed demonstrations in multi engine airplanes should be conducted in Vmca Stal First Stall Speed Recovery May Be Ottficult Published Vmca Yaw First INDICATED AIRSPEED þ Relationship Between Stall...

Page 279: ...d below which an engine should not be intentionally rendered inoperative for practice purposes was established because of the apparent practice of some pilots instructors and examiners of intentionally rendering an engine inoperative at a time when the airplane is being operated at a speed close to or below the power idle stall speed Unless the pilot takes immediate and proper corrective action un...

Page 280: ...er Vmca or stall warning which may be evidenced by inability to maintain longitudinal lateral or directional control aerodynamic stall buffet of stall warning horn sound recovery must be initiated immediately by reducing power to idle on operative engine and lowering the nose to regain Vsse Resume normal flight This entire procedure should be used at a safe altitude of at least 5 000 feet above th...

Page 281: ... against intentional spins The pilot of an airplane placarded against intentional spins should assume that the airplane may become uncontrollable in a spin since its performance characteristics beyond certain limits specified in the FAA regulations may not have been tested and are unknown This is why aircraft are placarded against intentional spins and this is why stall avoidance is your protectio...

Page 282: ...wing motion may develop even against full aileron and rudder resulting in the airplane becoming inverted during the onset of a spinning motion Once the airplane has been permitted to progress beyond the stall and is allowed to reach the rapid rolling and yawing condition the pilot must then immediately initiate the generally accepted spin recovery procedure for multi engine airplanes which is as f...

Page 283: ...center of gravity of the airplane is as far forward as possible Forward C G aids stall recovery spin avoidance and spin recovery An aft C G can create a tendency for a spin to flatten out which delays recovery 2 Whenever a student pilot will be required to practice slow flight or single engine maneuvers be certain that the qualified instructor pilot has a full set of operable controls in front of ...

Page 284: ...sse Recognize that under some conditions of weight density altitude and aircraft configuration a twin engine aircraft cannot climb or accelerate on a single engine Hence a single engine go around is impossible and the aircraft is committed to a landing Plan your approach accordingly 5 Remember that if an airplane flown under instrument conditions is permitted to stall or enter a spin the pilot wit...

Page 285: ... the engine may not respond to the throttle when it is desired to discontinue the descent Both problems are amenable to one solution maintain adequate power to keep cylinder head temperatures in the green range during descent and lean to best power mixture that is progressively enrich the mixture from cruise only slightly as altitude decreases This procedure will lengthen the descent of course and...

Page 286: ...ng in nature from each wing tip In tests vortex velocities of 133 knots have been recorded Encountering the rolling effect of wing tip vortices within two minutes after passage of large airplanes is most hazardous to light airplanes This roll effect can exceed the maximum counter roll obtainable in a light airplane The turbulent areas may remain for as long as three minutes or more depending on wi...

Page 287: ...ormal allowing the wheels to spin and dissipate the freezing moisture The landing gear should then be cycled up then down wait approximately five seconds and then retract again Caution must be exercised to insure that the entire operation is performed below Maximum Landing Gear Operating Airspeed Use caution when landing on runways that are covered by water or slush which cause hydroplaning aquapl...

Page 288: ...he pilot in pre flight planning would be as senseless as failing to inspect the integ rity of the control surfaces or any other vital part of the machine The pilot himself has the responsibility for determining his reliability prior to entering the airplane for flight When piloting an airplane an individual should be free of conditions which are harmful to alertness ability to make correct decisio...

Page 289: ...lcohol and various drugs decrease the brain s tolerance to hypoxia Your body has no built in alarm system to let you know when you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a given flight or how it will manifest itself Some of the common symptoms of hypoxia are increased breathing rate a light headed or dizzy sensation tingling or warm sensat...

Page 290: ...ility may also vary in the same individual from day to day or even morning to evening Use oxygen on flights above 10 000 feet and at any time when symptoms appear Depending upon altitude an hypoxic individual has a limited time to make decisions and perform useful acts even though he may remain conscious for a longer period If pressurization equipment fails at certain altitudes the pilot and passe...

Page 291: ...of respiration that may occur in individuals as a result of emotional tension or anxiety Under conditions of emotional stress fright or pain breathing rate may increase causing increased lung ventilation although the carbon dioxide output of the body cells does not increase As a result carbon dioxide is washed out of the blood The most common symptoms of hyperventilation are dizziness hot and cold...

Page 292: ... alcohol constriction of visual fields decreased ability to see under dim illuminations loss of efficiency of sense of touch decrease of memory and reasoning ability increased susceptibility to fatigue and decreased attention span decreased relevance of response increased self confidence with decreased insight into immediate capabilities Tests have shown that pilots commit major errors of judgment...

Page 293: ... a pilot may still be under influence eight hours after drinking a moderate amount of alcohol Therefore an excellent rule is to allow at least 12 to 24 hours between bottle and throttle depending on the amount of alcoholic beverage consumed DRUGS Self medication or taking medicine in any form when you are flying can be extremely hazardous Even simple home or over the counter remedies and drugs suc...

Page 294: ...nds at altitudes even under 10 000 feet where most light planes fly CARBON MONOX DEAND NIGHT VISION The presence of carbon monoxide results in hypoxia which will affect night vision in the same manner and extent as hypoxia from high altitudes Even small levels of carbon monoxide have the same effect as an altitude increase of 8 000 to 10 000 feet Smoking several cigarettes can result in a carbon m...

Page 295: ...tions Flight Service Stations or Airport Facilities and are very good sources of information and are highly recommended for study Some of these are titled Airman s Information Manual 12 Golden Rules for Pilots Weather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust to Safety Rain Fog Snow Thunderstorm TRW Icing Pilot s Weather Briefing Guid...

Page 296: ...r Some Hard Facts About Soft Landings Propeller Operation and Care Torque What it Means to the Pilot Weight and Balance An Important Safety Consideration for Pilots SPECIAL CONDITIONS MAINTENANCE Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion and or lack of lu...

Page 297: ...he earliest possible opportunity A clean dry surface is virtually immune to corrosion Make sure that all drain holes remain unobstructed Protective films and sealants help to keep corrosive agents from contacting metallic surfaces Corrosion inspections should be made most frequently under high corrosion risk operating conditions such as in areas of excessive airborne salt concentrations e g near t...

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