Raytheon Beechcraft SIERRA C24R Pilot Operating Handbook Download

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Published By

RAYTHEON AIRCRAFT COMPANY

P.O. Box 85

Wichita, Kansas 67201

U.S.A.

NOTE

Where Beech Aircraft Corporation or Beechcraft is

referred to in this publication, it will be taken to read

Raytheon Aircraft Company.

Exported under the authority of license exception: TSU.

"These commodities, technology or software were exported from the

United States in accordance with Export Administration Regulations.

Diversion contrary to U.S. law prohibited."

■

aytbeo■ Aircraft

......

llawker

1=:,

Member of GAMA

General Aviation

GAMA

Manufacturers Association

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Summary of Contents for Beechcraft SIERRA C24R

Page 1: ...it will be taken to read Raytheon Aircraft Company Exported under the authority of license exception TSU These commodities technology or software were exported from the United States in accordance with Export Administration Regulations Diversion contrary to U S law prohibited aytbeo Aircraft llawker 1 Member of GAMA General Aviation GAMA Manufacturers Association ...

Page 2: ...of the pilot during all flight operations This handbook includes the material required to be furnished to the pilot by CAR 3 AirRlane Seri 1I Number This handbook supersedes all BEECH published owner s manuals flight manuals and check lists issued for this airplane with the exception of FAA Approved Airplane Flight Manuals COPYRIGHT BqECH 1994 l P N 169 590025 15B Reissued November 1980 P N 169 59...

Page 3: ... Manual must be in the slrplsne for sll flight operations Part Number 169 590025 15BTC1 Subject Fuel Selector Installation Date 8 26 97 Note This page should be flied In 1he front of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual immediately fol lowing the Title page This page replaces any Log of Temporary Changes page dated prior to 1he date In 1he lower right corner of th...

Page 4: ...AFTER PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL B4 Revision July 1994 LOG OF REVISIONS Page Description Title Page Updated Page A B4 New 10 1 thru Revised Section X Safety 10 48 Information May 1994 r PAGE A ...

Page 5: ...ER PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 83 Revision October 1990 LOG OF REVISIONS Page Description Title Page Updated Page A 83 New 10 1 thru Revised Section X 10 48 Safety Information October 1990 PAGE A ...

Page 6: ...ed Table of Contents Revised Folio 1 6A and 1 6B Revised Use of the Handbook and Shifted Material 4 1 4 10 4 11 4 12 4 12A and 4 128 4 13 Revised Table of Contents Revised Before Takeoff and Takeoff and Shifted Material Revised Cruise and Leaning Mix ture Using the Exhaust Gas Tem perature Indicator EGT and Shift ed Material Revised Before Landing and Shifted Material Revised Shutdown and Shifted ...

Page 7: ...e Power Settings 2700 RPM 75 MCP or Full Throttle Table 5 24 thru 5 26 Shifted Material 5 27 Revised Cruise Speeds 5 28 Deleted Fuel Flow vs Brake Horse power and Shifted Material 7 1 Revised Table of Contents 7 3 Revised Table of Contents 7 10 7 11 Revised Flight Instruments Ground Control and Shifted Material 7 12 Shifted Material 7 29 Revised Alternator and Shifted Material 7 30 Revised Externa...

Page 8: ... 0 co X a Page 7 34 7 35 7 36 8 11 2 of 2 LOG OF REVISIONS Description Revised Ventilation Shifted Material Added New Page and Shifted Material Revised External Power Receptacle Page A I ...

Page 9: ...le Page Reissue A Page Reissue a and b Reissue 1 1 thru 1 19 Reissue 2 1 thru 2 29 Reissue 3 1 thru 3 13 Reissue 4 1 thru 4 16 Reissue 5 1 thru 5 34 Reissue 6 1 thru 6 19 Reissue 7 1 thru 7 35 Reissue 8 1 thru 8 43 Reissue Section 9 See Log of Supplements 10 1 thru 10 30 Reissue 10 1 Thru 10 67 Revised Safety Section Dated March 1981 B Page A ...

Page 10: ...y I important to have Safety Information in a condensed form in the hands of the pilots The Safety Information should be read and studied Periodic review will serve as a reminder of good piloting techniques WARNING Use only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources in connection with the maintenance and repair of Beech airplanes Genuine BEECHCRAFT pa...

Page 11: ... unacceptable stresses or temperatures or have other hidden damage not discernible through routine visual or usual nondestructive testing techniques This may render the part component or structural assembly even though originally manufactured by BEECHCRAFT unsuitable and unsafe for airplane use BEECHCRAFT expressly disclaims any responsibility for malfunctions failures damage or injury caused by u...

Page 12: ... 1 GENERAL SECTION 11 LIMITATIONS SECTION 111 EMERGENCY PROCEDURES SECTION IV NORMAL PROCEDURES SECTION V PERFORMANCE SECTION VI WEIGHT AND BALANCE EQUIPMENT UST SECTION VII SYSTEMS DESCRIPTION SECTION VIII HANDLING SERVICING AND MAINTENANCE SECTION IX SUPPLEMENTS SECTION X SAFETY INFORMATION June 1984 C ...

Page 13: ...I ...

Page 14: ...ce 1 8 Descriptive Data 1 9 Engine 1 9 Propeller 1 9 Fuel 1 9 Fue Tanks 1 10 Oil 1 10 Oil Capacity 1 10 Approved Oil Types 1 10 Maximum Certificated Weights 1 10 Cabin and Entry Dimensions 1 11 Baggage Space and Entry Dimensions 1 11 Specific Loadings 1 11 Symbols Abbreviations and Terminology 1 12 General Airspeed 1 12 Meteorological 1 14 Power 1 15 Engine Controls ana Instruments 1 15 Airplane P...

Page 15: ...Section I General 1 2 BEECHCRAFT SlerraC24R INTENTIONALLY LEFT BLANK June 1984 ...

Page 16: ...nual and or 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 must be operated and maintained in accordance with FAA Airworthiness Directives which may...

Page 17: ...e The handbook has been arranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions Section I Section II Section Ill Section IV Section V Section VI Section VII Section VIII Section IX Section X General Limitations Emergency Procedures Normal Procedures Performance Weight and Balance Equipment List Systems Description Handling Servicing and Maintena...

Page 18: ...s manual automatically 1 Original issues and revisions of BEECHCRAFT Service Bulletins 2 Original issues and revisions of FAA Approved Airplane Flight Manual Supplements 3 Reissues and Revisions of FAA Approved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Manuals and Pilot s Operating Handbooks This service is free and will be provided only to holders of this handbook...

Page 19: ...sions pages are used for maintaining a listing of all effective pages in the handbook except the SUPPLEMENTS section and as a record of revisions to these pages In the lower right corner of the outlined portion of the Log of Revisions is a box containing a capital letter which denotes the issue or reissue of the handbook This letter may be suffixed by a number which indicates the numerical revisio...

Page 20: ...ottom of the page this log will usually have the greater number of entries and discard the other tog VENDOR ISSUED STC SUPPLEMENTS When a new airplane is delivered from the factory the handbook wilt contain either an STC Supplemental Type Certificate Supplement or a Beech Flight Manual Supplement for all items requiring a supplement If a new handbook is purchased at a tater date for operation of t...

Page 21: ... Section I General 1 6B BEECHCRAFT SlerraC24R INTENTIONALLY LEFT BLANK June 1984 ...

Page 22: ...BEECHCRAFT Section I Sierra C24R General 25 9 IT 8 1 I 6 1 1 32 9 I f ________________ LI D i l 10 l 12 l THREE VIEW November 1980 1 7 ...

Page 23: ... Tip 26 feet 1Oinches Radius for Nose Wheel 12 feet 1 inch Radius for Inside Gear 4 feet 1 inch Radius for Outside Gear 16 feet 9 inches TURNING RADII ARE CALCULATED USING FULL STEERING ONE BRAKE AND PARTIAL POWER GROUND TURNING CLEARANCE 1 8 November 1980 I ...

Page 24: ...to battery switch refer to either BATTERY ALT switch or BATTERY switch depending upon configuration ENGINE One Avco Lycoming engine model I0 360 A1B6 II is a fueJ injected direct drive air cooled horizontally opposed 4 cylinder 200 horsepower rated engine Take off and Maximum Continuous Power Full Throttle at2700 RPM PROPELLER Hartzell constant speed two blade aluminum alloy propeller using HC M2Y...

Page 25: ...VED OIL TYPES Avco Lycoming Specification Number 301E approves for use lubricating oils which conform to both MIL L 60828 straight mineral type and MIL L 22851 ashless dispersant lubricants for airplane engines Refer to the Approved Engine Oils table in the HANDLING SERVICING AND MAINTENANCE section for a list of approved products MAXIMUM CERTIFICATED WEIGHTS Maximum Ramp Weight 2758 ibs Maximum T...

Page 26: ...ft 11 in Cabin Height maximum 4 ft Cabin Door 36 in x 38 in BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Volume 19 5 cu ft Door Width minimum 22 in Door Height minimum 33 in SPECIFIC LOADINGS Wing Loading at Maximum Take offWeight 18 84 lbs sq ft Power Loading at Maximum Take off Weight 13 75 lbs hp November 1980 1 11 ...

Page 27: ...r position and instrument error Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level Calibrated Airspeed expressed in knots Ground Speed is the speed of an airplane relative to the ground Indicated Airspeed is the speed of an airplane as shown on the airspeed indicator when corrected for instrument error IAS values published in this handbook assume zero instrument erro...

Page 28: ...e can be safely flown with the landing gear extended Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted Never Exceed Speed is the speed limit that may not be exceeded at any time Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution Stalling Speed or the minimum...

Page 29: ... International Standard Atmosphere in which 1 The air is a dry perfect gas 2 The temperature at sea level is 15 Celsius 59 Fahrenheit 3 The pressure at sea level is 29 92 inches Hg 1013 2 millibars 4 The temperature gradient from sea level to the altitude at which the temperature is 56 5 C 69 7 F is 0 00198 C 0 003566 F per foot and zero above that altitude Outside Air Temperature is the free air ...

Page 30: ...ition and instrument error In this handbook altimeter instrument errors are assumed to be zero Position errors may be obtained from the Altimeter Correction graph Actual atmospheric pressure at field elevation The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds Highest power rating not limited by...

Page 31: ... settings Tachometer Propeller Governor Indicates the rpm of the engine propeller Regulates the rpm of the engine propeller by increasing or decreasing the propeller pitch through a pitch change mechanism in the propeller hub AIRPLANE PERFORMANCE AND FLIGHT PLANNING Climb Gradient Demonstrated Crosswind Velocity 1 16 The ratio of the change in height during a portion of a climb to the horizontal d...

Page 32: ...ane from which all horizontal distances are measured for balance purposes A location along the airplane fuselage usually given in terms of distance from the reference datum The horizontal distance from the reference datum to the center of gravity C G of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reduci...

Page 33: ...at a given weight Fuel available for flight planning Fuel remaining after a runout test has been completed in accordance with governmental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard Empty Weight plus optional equipment Weight of occupants cargo and baggage Difference between Take off Weight or Ramp Weight if applicable and Basic Em...

Page 34: ...r 1980 Section I General Maximum weight exclusive of usable fuel The weight of chocks blocks stands etc used on the scales when weighing an airplane Points on the airplane identified by the manufacturer as suitable for supporting the airplane for weighing or other purposes ...

Page 35: ... _ ...

Page 36: ... 5 Propeller Specifications 2 6 Power Plant Instrument Markings 2 6 Miscellaneous Instrument Markings 2 7 Weight Limits 2 7 CenterofGravity Limits 2 7 Reference Datum 2 7 Maneuver Limits 2 7 Approved Maneuvers 2750 Pounds 2 8 Flight Load Factors 2750 Pounds 2 8 Takeoff 2 8 Minimum Flight Crew 2 8 Kinds of Operation Limits 2 8 Equipment Required for Various Conditions of Flight 2 8 Fuel Total Fuel ...

Page 37: ... II Limitations BEECHCRAFT SierraC24R The limitations included in this section have been approved by the Federal Aviation Administration and must be observed in the operation of this airplane 2 2 November 1980 ...

Page 38: ...action November 1980 IAS KTS MPH 168 193 143 165 125 144 96 110 135 155 113 130 Section II Limitations REMARKS Do Not Exceed This Speed in Any Operation Do Not Exceed This Speed Except in Smooth Air and Then Only With Caution Do Not Make Full or Abrupt Control Move ments Above This SP eed Do Not Extend Flaps or Operate With Flaps Ex tended Above This Speed Do Not Extend or Operate With Gear Extend...

Page 39: ...43 75 165 Normal Arc Operating Range Yellow 143 168 165 193 143 168 165 193 Operate With Arc Caution Only In Smooth Air Red 168 193 168 193 Maximum Line Speed For All Operations The limits of the arcs on the airspeed indicator are marked in GAS values POWER PLANT LIMITATIONS ENGINE One Avco Lycoming engine model IO 360 A186 Take off and Maximum Continuous Power _ Full Throttle at 2700 RPM 2 4 Nove...

Page 40: ...een or 100LL blue minimum FUEL ADDITIVES ALCOA TCP concentrate or equivalent mixed according to instructions provided by Alcor Inc OIL SPECIF CATIONS 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 HANDLI...

Page 41: ...GS OIL TEMPERATURE Caution Yellow Arc 60 to 120 F Operating Range Green Arc 120 to 245 F Maximum Red 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 FLOW Minimum Red Line 0 5 psi Operating Range Green Arc 4 0 to 16 6 gph Maximum Red Line 12 0 psi TACHOMETER No Extended Op...

Page 42: ...uctural Limitation Maximum Baggage Compartment Load 270 lbs CG LIMITS Gear Down Forward 110 inches aft of datum to 2375 pounds with straight line variation to 113 inches at 2750 pounds Aft 118 3 inches aft of datum at all weights REFERENCE DATUM Datum is 103 inches forward of wing leading edge MAC length is 52 7 inches MANEUVER LIMITS This is a normal category airplane Spins are prohibited No acro...

Page 43: ...ght maneuvering load factor flaps down 1 9G TAKEOFF Set 15 Flaps for Takeoff MINIMUM FLIGHT CREW One 1 Pilot KINDS OF OPERATION LIMITS 1 VFR day and night 2 IFR day and night EQUIPMENT REQUIRED 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 specify the minimum numbers and types of airplane instruments and equipment which must b...

Page 44: ...worthiness 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 etc However it ...

Page 45: ... IN KNOWN ICING CONDITIONS IS PROHIBITED LEGEND Numbers refer to quantities required Indicates that the item may be inoperative for the specified condition Refers to the REMARKS AND OR EXCEPTIONS column for explicit information or reference 2 10 November 1980 I ...

Page 46: ...T IN KNOWN ICING CONDITIONS IS PROHIBITED LEGEND Numbers refer to quantities required Indicates that the item may be inoperative for the specified condition Refers to the REMARKS AND OR EXCEPTIONS column for explicit information or reference 2 10 November 1980 ...

Page 47: ...worthiness 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 etc However it ...

Page 48: ... BEECHCRAFT Sierra C24R INTENTIONALLY LEFT BLANK November 1980 Section II Limitations 2 11 ...

Page 49: ...TRICAL POWER Battery System Alternator Starter Engaged Warning Light MC 731 and after VFR Dav VFR Night FR Day FR Night Remarks and or Exceptions Per FAR 91 33 Per FAR 91 33 1 1 1 1 1 1 1 1 1 1 1 1 May be inoperative provided ammeter is operative and monitored Cf l Ill 0 0 Ill al m ffl ii C t iil C O ll N l _I ...

Page 50: ...ENT AND FURNISHING Seat belts and Shoulder harnesses Emergency locator transmitter FIRE PROTECTION Portable fire extinguisher Per Person or Per FAR 91 33 Per FAR 91 52 Optional en m ii m C t N C t tJ I r g 0 Ill er 0 I I Ill ...

Page 51: ...v VFR Nioht FR Day FR N7iiht Remarks and or Exceptions 1 1 1 1 May be inoperative for ferry flight provided tabs are visually checked in the neutral position prior to takeoff and checked for full range of operation 1 1 1 1 May be inoperative providing flap travel is visually inspected prior to takeoff 1 1 1 1 iii s 0 C l a m m ID C X Ill C C z II ij I ...

Page 52: ...low indicator ICE AND RAIN PROTECTION Emergency static air source Pilot heater 1 2 1 2 1 2 1 2 I One may be inoperative provided other side is operational and amount of fuel on board can be established to be adequate for the intended flight Optional Optional a ID ffl m mO 0 J t 0 a a r r ID r n a o UI I ...

Page 53: ...ion lights Landing gear warning horn I VFR Dav VFR Nioht FR Dav FR Nioht Remarks and or Exceptions 1 1 1 1 May be inoperative provided operations are continued only to a point where repairs can be accomplished Gear must be left down 4 4 4 4 1 1 1 1 2 Dis g en CD I m a C c Ill C t D I I ...

Page 54: ...FAR 91 33 J co Q Rotating beacon 1 1 Optional 0 Position light 3 3 NAVIGATION INSTRUMENTS Altimeter Airspeed indicator Vertical speed Magnetic compass 1 1 1 1 Attitude indicator 1 1 Turn and slip indicator 1 1 Directional gyro 1 t r Clock 1 1 f n ITransponder Per FAR 91 24 91 90 91 97 QI 0 Navigation equipment Per FAR 91 33 g Ill ...

Page 55: ...t air Vacuum gage ENGINE INDICATING INSTRUMENTS Engine tachometer indicator Exhaust gas temperature indicator Manifold pressure indicator VFR O v VFR Niaht FR Dav FR N qht Remarks and or Exceptions 1 1 1 1 1 1 1 1 Optional 1 1 1 1 Cf 5l DI 0 0 II a Cl Hl i J DI 0 lJ I J 5j l I ...

Page 56: ... BEECHCRAFT Sierra C24R en w I a I I 6 w z 8 z w 0 ni o 2 ni g u u Cl c Q Cl a E Q 0 66 November 1980 Section II Limitations 2 19 ...

Page 57: ...ull Capacity 59 8 gallons Usable 57 2 gallons Value given is nominal Tank capacity will vary with tem perature and manufacturing tolerances FUEL MANAGEMENT Do not take off when Fuel Quantity indicators indicate in the yellow band on either indicator Maximum slip duration is 30 seconds 2 20 November 1980 ...

Page 58: ...OBATIC MANEUVERS INCLUDING SPINS APPROVED NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW MANEUVER BANK ANGLES NO MOU THAN 60 CHANDHlES lAlY 1GHTS 5TIEP TUIN5 STAU5 IEXCE 1 WHi STAllSI MAX1MUM ENTRY SPUD 125 KTS 1 MPH 115 KTS 1 MPH 115 KTl 144 MPH NOTE MAXIMUM ALTITUDE LOSS DUIING STALL SLOW DfCflEUTION JOO LANDING GEAR MAXIMUM GEAR EXTENDED SPEED 135 KTS 155 MPH MAXIMUM GIO OPERATING SP...

Page 59: ...4 MPH NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW MAN UVU 8ANI ANG LES NO MORE THAN 60 MAXIMUM ENTRY SPeED CHAN0EllES l 44t MPH lAlY ErCMH 144 MPH STEEP UR NS 14 4 MP i STAUS l XCfPT WHIP SIAU SI SLOW 0 CEl 1Aff0N NOTE MAX1MUM AH ITUDE lOSS OUIINC SJAtL 300 H LANDING GEAR MAXIMUM C AR EX IINO O PHO MAXIMUM ClAR O P RATINC SPUO EXlt NSIO...

Page 60: ...inches of mercury Monifold Press 4 Indicated Airspeed 87 KTS 100 MPH 5 Emergency Extension Valve OPEN L Use Handle Turn Counter Clockwise MC 449 MC 452 thru MC 536 except MC 533 EMERGENCY LANDING GEAR EXTENSION 1 Londing Geor Motor Circuit Breaker OFF Pull 2 G eor Position Switch DOWN 3 Thro de MAXIMUM 12 inches of mercury Manifold Press 4 Indicated Airspeed 100 MPH 5 Emergency Extension Valve OPE...

Page 61: ... serials which have complied with BEECHCRAFT SeNice Instructions No 1095 _ _ I _ T 0T I I I I oFF ___ Adjacent to Engine Instrument Cluster 7 1 00 N01 TAKE O FF WHEN fUtl QUAN TI TY GAUGE INOICAfES IN YHlO W O N J EITHE R GAUGE MAXIM UM SLI P DURAT ION 30 S EC On Upper Right Instrument Panel RAISE FLAPs 7 TO INCREASE BRAK E FFECTIVENES 2 24 November 1980 ...

Page 62: ...ved Airplane Flight Manual P N 169 590025 158 Reissued November 1980 or Subsequent MC 449 MC 452 and After The addition of a placard to the fue selector to warn of the no flow condition that exists between the fuel selector detents Insert this temporary change Into the C24R Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Immediately following page 2 24 Sec tion II LIMITATIONS an...

Page 63: ... Far e Of The Fuel Selector Valve For Those Airplanes In Compliance With S B 2670 WARNING POSITION SELECTOR IN OETENTS ONLY NO FUEL FLOW TO ENGINE BElWEEN DETENTS Approved 2 Of 2 A C Jackson Raytheon Aircraft Company DOA CE 2 P N 169 590025 15BTC1 August 26 1997 ...

Page 64: ...lap Switch or Left of Quadrant Control Pan 1 USE 15 FLAPS 1 L OR TAKE OFF_J On Pedestal Between Front Seats I 0 7 w r 7 NO i N 0 s E I I I I U I I p I I L L__ _ On Floorboard in Front of Pilot s Seat EMERGENCY GEAR EXTENSION II ACCESS DOOR ii November 1980 2 25 ...

Page 65: ... AIRSPHD STATIC SOURCE ON SEE PILOTS CHECK l lST EMU _ c lf OR fLIGHT MANUAL I EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER OFF CAUBRATION EUOR NORMAL L _J On Upper Right Instrument Panel i 7 IN CAS E OF FIRE IN ENGINE COMPARTMENT CLOSE DEFROST CABIN AIR VALVE L _J On Lower Left Sidewall Panel 2 26 lro LEVEL AIRCRAFT LEVE IBAGGAGE COMPARTMENT FLOOR I November 1980 ...

Page 66: ...IMUM CAPACITY _J On Aft Cabin Bulkhead r HAT SHELF 7 0 L NO HEAVY OBJECTS _J On Bulkhead Below Hat Shelf When 5th and 6th Seats are Installed 0 I j MAXIMUM FIFTH AND SIXTH SEAT STRUCTURAL CAPACITY 250 POUNDS REFER TO WEIGHT ANO BALANCE FOR LOADING INSTRUCTIONS NO SMOKING IN FIFTH AND SIXTH SEAT November 1980 2 27 ...

Page 67: ...TS SHORTER THAN 4 FT 7 IN DO NOT USE SHOULDER STRAP 2 PLACE SEAT BACK IN THE UPRIGHT POSITION DURING L TAKEOFF AND LANDING _j Adjacent to 5th and 6th Seats When Installed 1 7 INSTRUCTION SHOULDER STRAP l OCCUPANTS SHORTER THAN 4 FT 7 IN DO NOT USE SHOULDER STRAP L _J On Right Sidewall Below Third Window r NO SMOKING IN FIFTH AND SIXTH SEAT L_ __J 2 28 November 1980 ...

Page 68: ...on Right Side When Requir Jd by Weight and Balance Data BAGGAGE CARGO O R fAMll Y SEATS LOAD IN ACCORDANCE W ITH W EIGH T BALANCE DATA MAx1 Mu M SEAl CAPACITY _ _ __ __ POUNDS _J On Baggage Door Adjacent to Handle November 1980 1 7 PULL PIN ROTATE HANDLE TO OPEN L _J 2 29 ...

Page 69: ... ...

Page 70: ... 3 7 Emergency Descent 3 7 Maximum GlideConfiguration 3 7 Landing Emergencies Landing Without Power 3 8 Landing Gear Retracted With Power 3 8 Systems Emergencies Propeller Overspeed 3 9 Starter Engaged Warning Light Illuminated 3 9 Alternator Out Procedure 3 10 Unscheduled Electric ElevatorTrim 3 10 Landing Gear Emergency Extension 3 10 Landing Gear Retraction After Practice Manual Extension 3 11 ...

Page 71: ...Section Ill Emergency Procedures BEECHCRAFT SierraC24R INTENTIONALLY LEFT BLANK 3 2 November 1980 ...

Page 72: ...inimizes 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 occur in the op...

Page 73: ...ctor Valve OFF 4 Battery switch Alternator switch and Magneto Start switch OFF AFTER LIFTOFF AND IN FLIGHT Landing straight ahead is usually advisable If sufficient altitude is available for maneuvering accomplish the following 1 Mixture FULL RICH 2 Fuel Boost Pump ON 3 Fuel Selector Valve SELECT OTHER TANK feel for detent and check visually 4 Magnetos CHECK LEFT AND RIGHT THEN BOTH 3 4 NOTE The m...

Page 74: ...QUIRED 8 Landing Gear DOWN or UP depending on terrain 9 Battery switch alternator switch and Fuel Boost Switch OFF ENGINE DISCREPANCY CHECKS CONDITION ROUGH RUNNING ENGINE 1 Mixture FULL RICH then LEAN as required 2 Magneto Start Switch CHECK LEFT RIGHT THEN BOTH CONDITION LOSS OF ENGINE POWER 1 Fuel Flow Gage CHECK If fuel flow is abnormally low a Mixture FULL RICH b Auxiliary Fuel Pump ON Lean a...

Page 75: ...IRED 5 Fuel Boost Pump ON OR OFF as required 6 Magneto Start Switch BOTH NOTE When engine starts adjust throttle propeller and mixture controls ENGINE FIRE IN FLIGHT The red FIREWALL AIR 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 on the left of the power control quadrant must be pulled aft to close T...

Page 76: ...ND 1 Fuel Selector Valve OFF 2 Throttle CLOSE 3 Mixture IDLE CUT OFF 4 Battery Switch and Alternator Switch OFF 5 Magneto Start Switch OFF 6 Fire Extinguisher USE TO EXTINGUISH FIRE EMERGENCY DESCENT 1 Propeller FULL FORWARD High rpm position 2 Throttle IDLE 3 Landing Gear DOWN 4 Airspeed ESTABLISH 135 KTS 155 MPH MAXIMUM GLIDE CONFIGURATION 1 Landing Gear UP Landing gear safety switch OFF if syst...

Page 77: ...ENDING ON TERRAIN 6 Battery Switch and Alternator Switch OFF LANDING GEAR RETRACTED WITH POWER If possible choose firm sod or foamed runway Make a normal approach using flaps as necessary When sure of reaching the selected landing spot 1 Throttle CLOSED 2 Airspeed NORMAL APPROACH SPEED 3 Fuel Selector Valve OFF 4 Mixture IDLE CUT OFF 5 Flaps AS REQUIRED 6 Battery Switch and Alternator Switch OFF 7...

Page 78: ...ENGAGED warning light illuminates whenever the starter is engaged If this light remains illuminated after the Magneto Start Switch is released from the START position the starter relay is still energized Consequently electrical power is still being supplied to the starter and it remains engaged Continuing to supply power to the starter will eventually result in the complete loss of electrical syst...

Page 79: ...the battery switch alternator switch or alternator circuit breaker during flight is prohibited except as required by an actual emergency UNSCHEDULED ELECTRIC STABILATOR TRIM 1 Airplane Attitude MAINTAIN using stabilator control 2 Stabilator Trim Thumb Switch on Control Wheel DEPRESS AND MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM 3 Stabilator Trim ON OFF Switch on instrument panel OFF 4 Manu...

Page 80: ...Use Emergency Extension Wrench Turn Clockwise 2 LOG GEAR MOTOR Circuit Breaker PUSH IN 3 Landing Gear Switch Handle UP 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 exposed to moisture and or icing conditions ground obstructions not properly corrected may cause inflight ...

Page 81: ...pproximately 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 prevent it from swinging open SPINS SPINS ARE PROHIBITED If a spin is entered inadvertently Immediately move the control column full forward and simultaneously apply full rudder opposite to the direc...

Page 82: ...rument rated pilot who unavoidably encounters instrument conditions or in other emergencies such as severe turbulence If the landing gear is used at speeds higher than the maximum extension speed the gear should be left down until landing Inspection of the gear doors is required in accordance with maintenance procedures with repair if necessary November 1980 3 13 ...

Page 83: ... I I i I ...

Page 84: ...ooded Engine 4 8 After Starting And Taxi 4 9 Before Takeoff 4 9 Takeoff 4 10 Climb 4 11 Cruise 4 11 Leaning Mixture Using the Exhaust Gas 1 Temperature Indicator EGT 4 11 Descent 4 12 Before Landing 4 12 Balked Landing 4 12A After Landing 4 12A Shutdown 4 12A Environmental Systems 4 13 Heating and Ventilation 4 13 Cold Weather Operation 4 13 Preflight Inspection 4 13 Engine 4 14 Icing Conditions 4...

Page 85: ... Section IV Normal Procedures BEECHCRAFT SierraC24R INTENTIONALLY LEFT BLANK 4 2 November 1980 ...

Page 86: ...e of Climb Vx 71 KTS 82 MPH Best Rate of Climb Vy 85 KTS 98 MPH Landing Approach io KTS 81 MPH Balked Landing Climb 70 KTS 81 MPH Maximum Demonstrated Crosswind Component 17 KTS 20 MPH Maximum Turbulent Air Penetration Speed 125 KTS 144 MPH Take off Speeds Liftoff 66 KTS 76 MPH 50 Feet Above Runway 71 KTS 82 MPH PREFLIGHT INSPECTION CD Q I 0 l Nft flCl t U J November 1980 4 3 ...

Page 87: ...K e Position light CHECK 3 LEFT WING LEADING EDGE a Pilot 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 Cap SECURE 4 LEFT LANDING GEAR a Tire Wheel and Brake CHECK b Fuel Sump DRAIN use fuel drain tool 5 NOSE SECTION a left Cowl SECURE b Induction Air Intake CLEAR Filter CHECK condition and security ...

Page 88: ...eron CHECK b Flap CHECK c Fuel Tank Vent Line UNOBSTRUCTED 9 RIGHT FUSEUJ GE 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 FUSEUJ GE a Static Pressure Button UNOBSTRUCTED b All Antennas CHECK c Baggage Door SECURE BEFORE STARTING 1 Seats POSITION AND LOCK Seat Backs UPRIGHT 2 Seat B...

Page 89: ...AFT 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 either fuel quanity gage indicates in yellow arc EXTERN...

Page 90: ...y Power Unit CONNECT 3 Auxiliary Power Unit SET OUTPUT 13 75 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 NOTE MC 449 MC 452 thru MC 673 are 14 volt systems MC 674 and after are 28 volt sy...

Page 91: ...xture ADVANCE MIXTURE SLOWLY as engine starts firing regularly e Throttle RETARD to fast idle position 3 External Power if used DISCONNECT 4 Alternator Switch ON 5 Oil Pressure ABOVE RED RADIAL WITHIN THIRTY SECONDS 6 Warm up 1000 to 1200 RPM 7 Starter Engaged Warning Light if installed CHECK should be illuminated during start and extinguished after start 4 8 CAUTION If the STARTER ENGAGED Warning...

Page 92: ...Lycoming Service Bulletin No 245 BEFORE TAKEOFF 1 Parking Brake SET 2 Seat Belts and Shoulder Harnesses CHECK 3 Avionics CHECK 4 Engine Instruments CHECK 5 Flight Instruments CHECK and SET 6 Starter Engaged Warning Light if installed CHECK should not be illuminated If light is not installed or is inoperative the ammeter indication should be less than 25 of full charge at 1000 to 1200 rpm and shoul...

Page 93: ...HECK Make final check of manifold pressure fuel flow and rpm at the start of the take off run TAKEOFF Take Off Full Throttle 2700 RPM Cruise Climb Full Throttle 2700 RPM NOTE Do not take off or land with the Fuel Boost Pump ON The Fuel Boost Pump should be used only for starting and in the event of an emergency 1 Power SET take off power and mixture before brake release 2 Airspeed ACCELERATE to an...

Page 94: ...anner 1 lean the mixture and note the point on the indicator at which the temperature peaks and starts to fall a CRUISE LEAN MIXTURE Enrich mixture push mixture control forward until EGT indicator shows a drop of 25 F to 50 F on rich side of peak b BEST POWER MIXTURE Enrich mixture push mixture control forward until EGT indicator shows a drop of 75 F to 100 F on rich side of peak CAUTION Do not co...

Page 95: ...ccordingly In very cold weather EGT s 25 F rich of peak may not be obtainable DESCENT 1 Altimeter SET 2 Power AS REQUIRED avoid prolonged idle settings and low cylinder head temperatures 3 Mixture ENRICH 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 fee...

Page 96: ... THROTTLE 2700 RPM 4 Landing Gear UP 5 Airspeed 70 KTS 81 MPH until clear of obstacles then TRIM TO BEST RATE OF CLIMB SPEED 6 Flaps UP AFTER LANDING 1 Landing and Taxi Lights AS REQUIRED 2 Flaps UP 3 Trim Tab SET TO 0 SHUTDOWN 1 Parking Brakes SET 2 Electrical and Avionics Equipment OFF 3 Throttle CLOSE 4 Mixture IDLE CUT OFF 5 Magneto Start Switch OFF after engine stops 6 BATTERY ALT Switch OFF ...

Page 97: ... Section IV Normal Procedures BEECHCRAFT Sierra C24R INTENTIONALLY LEFT BLANK 4 12B June 1984 r ...

Page 98: ...he SYSTEMS DESCRIPTION Section for operation of heating and ventilation controls COLD WEATHER OPERATION PREFLIGHT INSPECTION All accumulations of ice snow and frost must be removed from the wings tail control surfaces and hinges propeller windshield fuel cell filler caps crankcase vents and fuel June 1984 4 13 ...

Page 99: ...n the HANDLING SERVICING AND MAINTENANCE Section WARNING Ascertain that magneto switch and battery master switch are off before moving propeller by hand Always pull the propeller through by hand opposite the direction of rotation several times to clear the engine and limber up the cold heavy oil before using the starter This will also lessen the load on the battery if external power is not used Un...

Page 100: ...bility of congealed oil NOTE It is advisable to use external power for starting in cold weather During warm up monitor engine temperatures closely since it is quite possible to exceed the cylinder head temperature limit in trying to bring up the oil temperature Exercise the propeller several times to remove cold oil from the pitch change mechanism The propeller should also be cycled occasionally i...

Page 101: ...he 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 avoid other ...

Page 102: ...I I ...

Page 103: ...System 5 13 Fahrenheit to Celsius Temperature Conversion 5 14 ISA Conversion 5 15 Stall Speeds Power Idle 5 16 Wind Components 5 17 Take OffDistance Hard Surface 5 18 Take Off Distance Grass Surface 5 19 Normal Climb 5 20 Time Fuel and Distance to Climb 5 21 Cruise Power Settings 2700 RPM Full Throttle 5 22 2700 RPM 75 MCP Or Full Throttle 5 23 2500 RPM 75 MCP Or Full Throttle 5 24 2400 RPM 65 MCP...

Page 104: ... SUBJECT BEECHCRAFT Sierra C24R PAGE Range Profile 57 Gallons 5 30 Endurance Profile 37 Gallons 5 31 Endurance Profile 57 Gations 5 32 Landing Distance Hard Surface 5 33 Landing Distance Grass Surface 5 34 5 2 November 1980 ...

Page 105: ...re detailed below All examples and calculations utilize the following conditions CONDITIONS At Denver Outside Air Temperature 15 C 59 F Field Elevation 5330 ft Altimeter Setting 29 60 in Hg Wind 270 at 10kts Runway 26L length 10 010 ft J Route of Trip DEN V81 AMA For VFR Cruise at 11 500 feet WIND OAT 11 500 11 500 ROUTE MAGNETIC DIST FEET FEET SEGMENT COURSE NM OIR KTS c DEN COS 151 55 010 30 5 C...

Page 106: ... 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 DEN 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 AMA 5 4 29 92 29 56 36 in Hg The pressure altitude at AMA is 360 feet above the field elevation 3605 360 3965 ft NOTE For flight planning the diffe...

Page 107: ...presented for a standard day ISA 20 C 36 F above a standard day ISA 20 C and 20 C 36 F below a standard day ISA 20 C These should be used for flight planning The IOAT values are true temperature values which have been adjusted for the compressibility effects IOAT should be used for setting cruise power while enroute Enter the graph for ISA CONVERSION at 11 500 feet and the temperature for the rout...

Page 108: ...OW TAS PRESS FLOW TAS FEET IN HG GPH KNOTS IN HG GPH KNOTS 11000 20 0 9 8 136 20 0 9 5 136 12000 19 2 9 7 134 192 93 134 Interpolate for 11 500 feet and the temperature for the appropriate route segment Results of the interpolations are 5 6 MAN FUEL ROUTE PRESS FLOW TAS SEGMENT IN HG GPH KNOTS DEN PUB 19 6 9 7 135 PUB TBE 19 6 9 6 135 TBE DHT 19 6 9 5 135 DHT AMA 19 6 9 4 135 NOTE The above are ex...

Page 109: ...EED ALTITUDE CRUISE SEGMENT NM KNOTS HRS MIN GAL DEN COS 2s 163 10 1 6 COS PUB 40 162 15 2 4 PUB TBE 74 121 37 5 9 TBE DHT 87 123 42 6 7 DHT AMA 65 125 31 4 9 Distance required to climb has been subtracted from segment distance TIME FUEL DISTANCE TIME FUEL DISTANCE ITEM HRS MINS GAL NM Start Runup Taxi and Take off acceleration 0 00 1 3 0 Climb 15 2 8 27 Cruise 2 15 21 5 294 Total 2 30 25 6 321 No...

Page 110: ...equired for the trip from the ramp weight Assumed ramp weight 2758 lbs Estimated fuel from DEN to AMA lbs gal 153 6 lbs 25 6 gal 6 Estimated landing weight 2758 154 2604 lbs Examples have been provided on the performance graphs The above conditions have been used throughout Rate of climb was determined for the initial cruise altitude conditions COMMENTS PERTINENT TO THE USE OF PERFORMANCE GRAPHS 1...

Page 111: ...The associated conditions define the specific conditions from which performance parameters have been determined They are not intended to be used as instructions however performance values determined from charts can only be achieved if the specified conditions exist 5 The full amount of usable fuel is available for all approved flight conditions 6 Engine and component cooling has been demonstrated ...

Page 112: ...1io 120 130 1 io IAS INDICATED AIRSPEED KNOTS 60 70 80 90 100 110 120 130 140 150 160 IAS INDICATED AIRSPEED MPH EXAMPLE IAS FLAPS GAS 150 130 ij 140 1 130 fil 120 w 8 110 o 100 90 80 J 70 J j 60 50 J b 120 z I 110 0 ill 100 Cl 90 0 80 gJ 70 i_ U 60 Cl 3 50 70 KTS 81MPH 15 69 KNOTS 79MPH 94 1 i flAPSW 40 50 s o 10 1io 90 100 110 120 IAS INDICATED AIRSPEED KNOTS so 10 80 90 160 110 120 1 io 1 io IA...

Page 113: ...1III111ttfffl V IERGENCYSYSTEM 85 KTS 98 MPH I 160 80 KTS 92 MPH 150 140 w 1 l 130 I 110 ill 10 90 _1 80 Id 0 70 1 Fi A PS UP_ Qj 60 oo 10 a o oo 100 do 120 i io 1 0 1so 1so 1io 170 c 160 a 150 I 140 ilj z 3 130 a 1 tn WI z 110 w c o c 100 zw w 90 60 70 60 1 5 z I 0 Wl l W 11 Q 1 t z ow wC I BO 1 70 50 sh o e o 90 100 do 120 I i 0 IAS INDIC ATED AIRSPEED NOTS NORMAL SYSTEM IAS INDICATED AIRSPEED K...

Page 114: ...RESSUREALTITUDE 6000 FT ALTIMETER CORRECTION 8 FT CORRECTEDALTITUDE 5992 FT 0 10 20 30 40 50 60 70 80 FLAPS DOWN O ri 60 70 80 90 100 110 120 130 140 150 160 170 50 60 70 80 90 HiO 110 IAS INDICATED AIRSPEED KNOTS IAS INDICATED AIRSPEED KNOTS 70 80 90 100 110 120 130 140 150 160 170 180 190 200 IAS INDICATED AIRSPEED MPH I I I I I I I I 60 70 80 90 100 110 120 130 IAS INDICATED AIRSPEED MPH g i 0 ...

Page 115: ... 0 uo a a 60 w u f f 70 5 80 90 FLAPS UP co 60 70 80 90 100 110 120 130 140 150 160 170 IAS INDICATED AIRSPE ED KNOTS 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 IAS INDICATED AIRSPEED MPH w 0 iiE wf u 1 0 w z f 0 C 52 uo wz a a 00 ua WU O f U t f f J co 0 11 11 11 1111 11111 ti 111111 IJB ffi 10 20 LAPS DOWN 35 30 40 50 60 70 1111111111111 80 90 50 60 70 80 90...

Page 116: ...i z 3 i g FAHRENHEIT TO CELSIUS TEMPERATURE CONVERSION 50 40 30 20 10 0 10 20 30 40 50 60 60 50 40 io io io o 10 20 JO 40 i o eo io so 90 100 110 120 DEGREES F I 1ff s a 0 3 l 2 m CJ m m cg 0 J Ill 0 o xi N ...

Page 117: ...V Performance 9l t09 0J S o a 1 j f g 0 0 1 s I rtRti t q J t sl r I t 0 M l e s1 t1 ITTtt rtt li cs s1 f t r lt i I sl 1 1 i f tt t s p t P a P I j f l T r T o K I 1 r I s tt i H H t t 1 11 H f r t Vi L t L I 0 J 33 300J JJ llf 31 10SS31 ld i i r r j t t I 1 H I I T H 0 0 0 I w a 0 a w 0 0 lw 0 N I 0 M I g I 0 f g I November 1980 5 15 ...

Page 118: ...EED IAS 59 KTS 68 MPH DI 3 120 WAS 300 FEET 1 110 n 90 1 00 en I I 0 so 190 I I Cl 0 UJ re tl11 t l I en w J w 7 _ WGEAR UP FL J Cl P J f en GEAR up F PS UP I 60 en 70 DbWN GEAR lAPS 15 z GE N FLAPS IS l Aflo m H t t fr9W F 50 G1 4F D lAp 35 en m t OWNFLA t m 3 PS35 i g it iil H 40 I I I lJ 2700 2500 2300 2100 1900 0 10 20 30 40 50 60 I I WEIGHT POUNDS ANGLE OF BANK DEGREES I l I f I ...

Page 119: ...0 z 0 EXAMPLE W INO SPEED 20 KTS ANGLE BETWEEN WIND DI RECTION AND FLIGHT PATH so HEADWIND COMPONEN T 13 KTS CROSSWI ND COMPONENT 15 KTS FLIGHT PATH 40 30 20 10 0 10 t t 2 0 6 0 t t H 70 I I c 10 20 170 1so 0 1so0 t 160 W I I I 0 10 140 130 I _ I I 20 I I 1100 120 H 11 I I 30 CROSSWIND COMPONENTS KNOTS 40 November 1980 5 17 ...

Page 120: ... 1 1 111 1 1 11 111 1 ll tlt l ffl E i Jo s 10 sl t t I 10 Ji 20 lo 6 10 20 30 4b 50 2700 2500 2300 OUTSIDE AIR TEMPERATURE C WEIGHT POUNDS I I I I I I I I I I I I I I I I I 40 20 0 20 40 60 80 100 120 OUTSIDE AIR TEMPERATURE F 2100 OAT 15 C 59 F PRESSURE ALTITUDE 5650 FT TAKE OFFWEIGHT g750 LBS HEADWIND COMPONENT 9 5 KTS GROUND ROLL 1600 FT TOTALDISTANCEOVERASOFTOBSTACLE 2290 FT t ttftttle 1 r 60...

Page 121: ...i f I rl L 0 J l t El i osj p 13 t _ _ _ W o o _ lU er w ii I I I I I I I 40 30 20 10 0 10 20 30 40 50 2700 2500 2300 OUTSIDE AIR TEMPERATURE c WEIGHT POUNDS I I I I I I I I I I I I I I II I 40 20 0 20 40 60 80 100 120 OUTSIDE AIR TEMPERATURE F OAT 15 C 59 F PRESSURE ALTITUDE 5650 FT TAKE OFF WEIGHT 2750 LBS HEADWIND COMPONENT 9 5KTS GROUND ROLL 1850 FT TOTAL DISTANCE OVER A 50 FTOBSTACLE 2580 FT ...

Page 122: ...T 15 C 59 F PRESSURE AlTITUDE 5650 FT WEIGHT 2750 LBS RATE OF CLIMB 570 FT MIN CLIMB GRADIENT 6 2 CLIMB SPEED 85 KTS 98 MPH 2000 20 1500 0 2 15 I f f 1000 u 2 w I 10 CD a I a CD 5 u 0 f ffffElT w f 0 a 1 o I I I 70 60 50 r r 40 io 20 io a 10 l20 30 OUTSIDE AIR TEMPERATURE C i I I I I I I I I I I I I 40 s o 60 ffllHBJllljlllljlli 500 1 1 50 0 50 100 150 2700 2500 2300 2100 OUTSIDE AIR TEMPERATURE F...

Page 123: ...R TEMPERATURE C 40 I I I I I I I I I I I I I I I I 100 so o sot I I 100 OUTSIDE AIR TEMPERATURE F 50 60 I I I 6 r 0 b OATAT CRUISE s c 23 F AIRPORT PRESSURE ALTITUDE 5650 FT CRUISE ALTITUDE 11 500 FT INITIAL CLIMB WEIGHT 2750 LBS TIMETOCLIMB 23 8 15 MIN FUEL TO CLIMB 28 5 11 5 a 17 LBS DISTANCE TO CLIMB 40 13 27 NM i 1 2 7 trrr i 1 0 20T 3 0 40 50 TIME TO CLIMB MINUTES I i I 1 1 J 10 20 iO io 50 L...

Page 124: ... FLOW TAS IOAT I MAN I FUEL PRESS FLOW TAS IOAT MAN I FUEL PRESS FLOW TAS NOTES 1 Shaded area represents operation with full throttle 2 Manifold Pressure values are approximate 3 Engine will be operating at 5 above rated power based on a manifold pressure increase of 1 in Hg due to ram rise Leaning not approved in dashed area use full rich only 2 ...

Page 125: ...1 3 61 10 2 127 146 48 9 22 0 61 10 2 130 150 84 29 22 5 61 10 2 133 153 5000 9 13 21 1 61 10 2 128 147 45 7 21 7 61 10 2 131 151 81 27 22 3 61 10 2 134 154 6000 5 15 20 9 61 10 2 129 148 41 5 21 5 61 10 2 132 152 77 25 22 1 61 10 2 135 155 7000 1 17 20 7 61 10 2 131 151 37 3 21 3 61 10 2 133 153 73 23 21 9 61 10 2 136 157 8000 2 19 20 5 61 10 2 132 152 34 1 21 1 61 10 2 135 155 70 21 21 8 61 10 2...

Page 126: ...1 10 2 127 146 52 11 23 6 61 10 2 129 148 83 31 24 2 61 10 2 132 152 4000 12 11 22 7 61 10 2 128 147 48 9 23 4 61 10 2 130 150 84 29 24 0 61 10 2 133 153 5000 9 13 22 5 61 10 2 129 148 45 7 23 1 61 10 2 131 151 81 27 23 7 61 10 2 134 154 6000 5 15 22 3 61 10 2 130 150 41 5 22 9 61 10 2 132 152 77 25 23 5 61 10 2 135 155 7000 1 17 22 1 61 10 2 131 r A U r 8000 l ii t r 1 1t i l f t ili il r i i J l...

Page 127: ...0 124 143 5000 7 14 20 9 54 9 0 120 138 43 6 21 5 54 9 0 123 142 81 27 22 2 54 9 0 125 144 6000 3 16 20 7 54 9 0 121 139 41 5 J 1 3 54 9 0 124 143 n 25 22 0 54 9 0 126 145 7000 1 17 20 5 54 9 0 122 140 37 3 21 1 54 9 0 125 144 73 23 21 7 54 9 0 126 145 8000 2 19 20 3 54 9 0 123 142 34 1 20 9 54 9 125 144 70 21 21 5 54 9 0 127 146 9000 6 21 20 1 54 9 0 124 143 30 1 20 7 54 9 126 145 66 19 21 3 54 9...

Page 128: ...112 129 79 26 18 4 48 8 0 111 128 39 4 18 9 48 8 0 113 130 75 24 18 2 48 8 0 111 128 36 2 18 7 48 8 0 113 130 72 22 18 0 48 8 0 11 2 129 32 0 18 5 48 8 0 114 131 68 20 17 8 48 8 0 113 130 28 2 18 3 48 8 0 114 131 64 18 17 6 48 8 0 114 131 25 4 18 1 48 8 0 115 132 61 16 17 5 48 8 0 114 131 21 6 18 0 48 8 0 116 134 57 14 17 3 48 8 0 115 132 18 8 17 8 48 8 0 116 134 55 13 17 1 48 8 0 115 132 14 10 17...

Page 129: ...SSURE ALTITUDE POWER SETTING FULL THROTTLE 2700 RPM TEMPERATURE STANDARD DAY ISA TRUE AIRSPEED 135 KNOTS 14 000 T 156 W _P _H 13 000 12 000 11 000 10000 9000 w 8000 0 7000 5 w 6000 a i l 5000 fl a 4000 3000 2000 1000 SL 105 110 115 120 125 130 135 140 145 TRUE AIRSPEED KNOTS 120 130 140 150 160 170 TRUE AIRSPEED MPH December 1982 5 27 ...

Page 130: ...ETTINGS 1700 HIOO iRECOMMENDED VALUES OF MANIFOLD PRESSURE AND RPM FOR CRUISE POWER SETTINGS 1900 2000 2100 2200 EXAMPLE ENGINESPEED MANIFOLD PRESSURE 2700 RPM 23 IN HG WITHIN RECOMMENDED LIMITS 2300 H tRECOMME r lbEb VALuE s oF MANIFOLD PRESSURE 0 AND RPM FOR CRUISE POWER SETTINGS 2400 2500 2600 2700 ENGINE SPEED RPM i I ff i l 0 0 3 g m m c iil D I I ...

Page 131: ...F s f f t RANGE INCLUDES START TAXI C IM c WITH 45 MINUTES RESERVE FUEL AT 55 MAXIMUM CONTINUOUS 15 000 Gj w II III II IIIIIIIIIiti l EII IIIll 11111 1 POWER LL l w 10 000 CRUISE TAS KNOTS I I I I I I I Cl t J w a I I w a c 5000 135 Hi 34 i125Hlt1141 c ltttt R C J w 1 T l IIYW J j 11 111111111111111 12 ti t tt W l W 360 380 400 420 440 RANGE NAUTICAL MILES ZERO WIND J CD iii ffl m Ill c II II 1 a ...

Page 132: ...ADING 57 U S GAL 342 LBS 15 000 Iii NOTE RANGE INCLUDES START TAXI AND CLIMB WITH 45 MINUTES RESERVE FUEL AT 55 MAXIMUM CONTINUOUS POWER w u e i io v 1 u I t OO 11 10 000 5000 f J t 1 tJ 7 J h H L J L 1 1 ff t t t1 J AS KNOTS E w C w C a tt tttt sL f 7 i21W 2s1 1 a l21js FHf 19sl 11111111111 l 600 620 640 660 680 700 RANGE NAUTICAL MILES ZERO WIND g s 0 0 0 3 0 D m CJ m m D C c iil C C lJ I 5l ...

Page 133: ...S 222 LBS 15 000 Iii w LL l w 10 000 0 f w a 5000 Cl Cl w a a SL 2 0 2 5 135 a r I o o 1 t f fi IV V f5ffi l ENDURANCE INCLUDES START TAXI AND CLIMB WITH 45 MINUTES RESERVE FUEL AT 55 MAXIMUM CONTINUOUS POWER 1 v 4 J 1 34 128 125 116 CRUISE TAS KNOTS 134 125 114 ffi t l 111 it n1 ot th 11 126 t 118 I 108 I I I I I I 3 0 3 5 4 0 4 5 ENDURANCE HOURS S m CD ffl m iil 0 o c o 0 0 ti CD I a r n 3 DI O ...

Page 134: ...342 LBS 15 000 NOTE ENDURANCE INCLUDES START TAXI AND CLIMB WITH 45 MINUTES RESERVE FUEL AT 55 MAXIMUM CONTINUOUS POWER Iii I Hill 134 v 128 125J O 116 CRUISE TAS KNOTS v io o Y w u 1 10 000 w 5000 er a SL I 3 5 4 b jO Y f v 0 z1 0 0 s iO 1 JJ rf 1 1 25 135 0 0 0 0 J 130 122 J r 126 118 I I I I 4 5 5 o 5 5 ENDURANCE HOURS 114 J 111 108 I I 6 o s 5 7 0 re a g _ 0 3 I l il IJJ u m __m D 0 z iii 0 0 ...

Page 135: ...81 HEADWIND COMPONENT 12 KTS 66 75 GROUND ROLL 750 FT 62 71 TOTALOVER50FTOBSTACLE 1400 FT 58 67 APPROACH SPEED 68 KTS 78 MPH H H H H f 1 rrn r n d f l 2500 RESSURe ALTITUDE FEET 000 0 SI il IISA 40 30 20 10 o 10 20 T 3o 40 OUTSIDE AIR TEMPERATURE C 7 T T U1 50 50 100 OUTSIDE AIR TEMPERATURE F w c zl w U z t w O w u W Jrl 50 60 2700 2500 2300 WEIGHT POUNDS g 1 ti 2100 li H _ tti I ti e ffl J ik 9Yi...

Page 136: ... a I w o 1 a a r t lt t 2750 2500 2300 2100 70 66 62 58 81 75 71 67 HEAD WINO COMPONENT GROUND ROLL TOTAL OVER 50 FTOBSTACLE APPROACH SPEED 21 1 s f E l a 1 1m 1 Y I 1080 FT 1730 FT 68 KTS 78 MPH 2500 l 2000 tii w u 1500 1 UJ 0 z o 1000 0 I o JO 20 10 o 10 20 T io 40 so 60 OUTSIDE AIR TEMPERATURE c I I I I I I I I I I I I I I I I 1 MI I Ii ilfPN f llflmtl I 500 2700 2500 2300 2100 50 O 50 100 OUTS...

Page 137: ... ...

Page 138: ...asicWeight And Balance Form 6 7 Weight And Balance Record 6 9 Weight And Balance Responsibilities 6 11 Moment Limits Vs Weight Graph 6 12 Computing Procedure 6 14 Sample Weight And Balance Loading Form 6 15 Weight And Balance Loading Form 6 16 Useful Load Weights And Moments Occupants 6 17 Usable Fuel 6 18 Equipment List Provided For Each Airplane November 1980 6 1 ...

Page 139: ... Section VI Wt Bal Equip List BEECHCRAFT Sierra C24R INTENTIONALLY LEFT BLANK 6 2 November 1980 ...

Page 140: ...alled Basic Empty Weight and Balance When the airplane 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 When the airp...

Page 141: ...ty of the airplane s operator 1 Three jack points are provided for weighing two on the wing front spar at Fuselage Station 129 2 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 1...

Page 142: ...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 129 5 for main wheels and Fuselage Station 57 6 for the nose wheel 7 Jack point weighings are accomplished by placing scales on the jack points specified in step 1 above Since the center of gravit...

Page 143: ...I TAIL TIE DOWN LEVEL POINT F S 285 9 1 rl JACK POINT BAGGAGE FLOOR ii F S 129 2 A I J B i I C F S 126 438 A NOSE TO LUMB BOB B DATUM TO PLUMB BOB C DATUM TO MAIN GEAR 24 605 6 g ll l m o Al m c C if a en m ii c Alo a N I ...

Page 144: ...____ JACK POINT LOCATION PREPARED BY FORWARD 129 2 Company AFT 285 9 Signature __________ SCALE NET READING TARE WEIGHT ARM MOMENT Space below provided for additions and subtractions to as weighed condition LESS 8 QT OIL 15 0 50 750 EMPTY WEIGHT ENGINE OIL 15 0 50 0 750 t UNUSABLE FUEL 15 6 125 0 1950 BASIC EMPTY WEIGHT a CD m m ii l 0 0 t NO 0 0 Qo m mCl a CD c n Cg r i s ...

Page 145: ... is a suitable means for meeting both requirements The current equipment list and basic empty weight and CG 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 basic empty wei...

Page 146: ...AL NO _______ REGISTRATION NO _______ PAGE NO _____ WEIGHT CHANGE RUNNlNG BASIC DATE ITEM NO DESCRIPTION OF ARTICLE ADDED OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 a ii ffl m iiJ 0 0 c NO i J J Ro jg C n 0 g r iii ...

Page 147: ...L NO REGISTRATION NO _______ PAGE NO _____ WEIGHT CHANGE RUNNING BASIC DATE ITEM NO DESCRIPTION OF ARTICLE ADDED OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS IN l 100 LBS 100 ___ e Cl ID Ro 2 ms I m c C r DJ Cl m iii 0 c Alo 0 x N o l I ...

Page 148: ...are shown on the Useful Load Weights and Moments tables The minimum and maximum 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 that the 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 i...

Page 149: ...400 2300 2200 Q a a g 2100 2000 1900 1800 WEIGHT VS MOMENT LIMITS 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2900 2900 3000 3100 3200 3300 3400 3500 LOAOEO AIRPI ANE MOMENT 100 12d 60J 7 ff QD l CD o Dl e m D C C r CD m CD 0 J Dl 0 0 JJ N l I ...

Page 150: ...973 3135 1860 2046 2200 2260 2486 2674 2660 2987 3147 1870 2057 2212 2270 2497 2685 2670 3000 3159 1880 2068 2224 2280 2508 2697 2680 3013 3170 1890 2079 2236 2290 2519 2709 2690 3027 3182 1900 2090 2248 2300 2530 2721 2700 3040 3194 1910 2101 2260 2310 2541 2733 2710 3054 3206 1920 21 12 2271 2320 2552 2745 2720 3067 3218 1930 2123 2283 2330 2563 2756 2730 3081 3230 1940 2134 2295 1340 2574 2768 ...

Page 151: ...required for start taxi and takeoff Add the Fuel Loading Condition to Zero Fuel Condition to obtain the SUB TOTAL Ramp Condition 5 Subtract the fuel to be used for start taxi and takeoff to arrive at the SUB TOTAL Take off Condition 6 Subtract the weight and moment of fuel to be used from the take off weight and moment The SUB TOTAL Condition of No 3 and No 5 as welt as the landing condition momen...

Page 152: ...40 374 3 3rd 4th SEAT OCCUPANTS 340 482 4 5th 6th SEAT OCCUPANTS 130 222 5 BAGGAGE 6 CARGO 7 SUB TOT 2530 2990 8 FUEL L f NG 32 gal 192 225 9 SUB TOTAL RAMP CONDITION 2722 3215 10 LESS FUEL FOR START TAXI and TAKE OFF 8 9 11 SUB TOTAi TAKE OFF CONDITION 2714 3206 12 LESS FUEL TO DESTINATION 25 gal 150 176 13 LANDING CONDITION 2564 3030 Fuel for start taxi and take off is normally 8 lbs at an avera...

Page 153: ...MPTY CONDITION 2 FRONT SEAT OCCUPANTS 3 3rd 4th SEAT OCCUPANTS 4 5th 6th SEAT OCCUPANTS 5 BAGGAGE 6 CARGO 7 SUB TOTAL 8 FUEL LOADING 9 SUB TOTAL RAMP CONDITION o LESS FUEL FOR START TAXI AND TAKE OFF 11 SUB TOTAL TAKE OFF CONDITION 2 LESS FUEL TO DESTINATION 3 LANDING CONDITION Fuel for start taxi and take off is normally 8 lbs at an average mom 100 of 9 6 16 November 1980 ...

Page 154: ... back in full up position ARM 112 MOM 100 134 146 157 168 179 190 202 213 224 3RD AND 4TH SEATS BENCH SEAT SPLIT SEAT ARM ARM 142 144 MOM MOM 100 loo 170 173 185 187 199 202 213 216 227 230 241 245 256 259 270 274 284 288 7 Values computed from a C G criterion based on a 170 pound male Differences in physical characteristics can cause variation in center of gravity location ff m C C C c en C m J J...

Page 155: ... 27 30 32 35 37 40 45 50 52 57 6 18 5th 6th SEATS ARM 171 Moment Weight 100 137 140 154 f50 171 160 188 170 205 180 222 190 200 USABLE FUEL ARM 117 WEIGHT 30 60 90 120 132 150 162 180 192 210 222 240 270 300 312 342 Moment 100 239 257 274 291 308 325 342 MOMENT 100 35 70 105 140 154 176 189 211 225 246 259 281 316 351 365 400 November 1980 ...

Page 156: ...OMENTS Weight 10 20 30 40 50 60 70 80 90 100 110 120 130 November 1980 BAGGAGE ARM 167 Moment Weight 100 17 140 33 150 50 160 67 170 84 180 100 190 117 200 134 210 150 220 167 230 184 240 200 250 217 260 270 Moment 100 234 251 267 284 301 317 334 351 367 384 401 418 434 451 6 19 ...

Page 157: ...SYSTEMS OESaFTION ...

Page 158: ...nual Trim 7 6 ElectricTrim 7 6 Instrument Panel 7 6 Illustration MC 449 MC 452 thru MC 536 exceptMC 533 7 7 Illustration MC 533 MC 537through MC 570 7 8 Illustration MC 571 andafter 7 9 Switches 7 10 Circuit Breakers 7 1 0 Flight Instruments 7 1o Ground Control 7 1 1 Wing Flaps Manual 7 11 Electric 7 11 Effect of Flaps on Flight Takeoff 7 12 Landing Gear 7 12 Control Switch 7 13 Position Indicator...

Page 159: ...houlder Harnesses 7 17 Doors and Exits Forward Cabin Doors 7 18 Aft Utility Door 7 19 Emergency Exits 7 19 Control Locks 7 19 Engine 7 20 Engine Controls 7 20 Engine Instruments 7 20 Manifold Pressure and Fuel Flow Indicator 7 20 Illustration 7 21 Exhaust Gas Temperature Indicator EGT 7 22 Engine Break in Information 7 22 Cowling 7 22 Lubrication System 7 23 Induction System Icing 7 23 Starter 7 2...

Page 160: ...9 External Power Receptacle 7 30 Lighting Systems Interior Lighting 7 31 Exterior Lighting 7 31 Environmental Systems Illustration 7 32 Cabin Heating 7 33 Ventilation 7 33 Exhaust Vent 7 34 Pitot and Static Systems Pitot System 7 34 Pilot Heat 7 34 Normal Static Air System 7 34 Emergency Static Air System 7 35 Vacuum System 7 35 Stall Warning System 7 35 December 1982 7 3 ...

Page 161: ... Section VII Systems Description BEECHCRAFT SierraC24R INTENTIONALLY LEFT BLANK 7 4 November 1980 ...

Page 162: ...t are available To adjust either of the front seats pull the release knob below the left forward seat corner pull to the right then up 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 three positions Outboard armrests for the front seats are attached to the cabin doors FLIGHT CO...

Page 163: ... trims the airplane s nose up ELECTRIC TRIM The optional electric stabilator trim system controls include the ON OFF circuit breaker type switch located on the instrument panel and a thumb switch on the control wheel The ON OFF switch must be in the ON position to operate the system The thumb switch must be depressed and moved forward for nose down aft for nose up and when released returned to the...

Page 164: ... BEECHCRAFT Sierra C24R November 1980 Section VII Systems Description ci G u a tsS C It 0 E I N It t 0 IE c t 0 _ w z c a 1 z w IE Ct I _ c u ii I 7 7 ...

Page 165: ... Section VII BEECHCRAFT Systems Description SierraC24R c c 0 _ u u Q iHJ 0 ni F o ii I _ u 1 1 8 0 ll J J 1 j ri u 0 w z o I z w i a I u o u 7 8 November 1980 ...

Page 166: ...SierraC24R November 1980 Section VII Systems Description f01 0il 01 0 1 0 Oi 0 0 _ L01 o _01i 0H 01 io 011 on 0 01 0 0i 0ji Oil 0 0 li l 0 10 0l 0 O 0 10i lm1l 01 i I i i Ill g Ill U 0 I w z Q 1 z w ii a t J a 7 9 ...

Page 167: ...ass is attached to the upper center of the windshield Ram air pressure for the airspeed indicator enters through the pitot tube under the left wing Static air pressure for the altimeter vertical speed and airspeed indicator is supplied by a static port on each side of the fuselage just aft of the baggage area IMC 449 MC 452 through MC 536 except MC 533 The instruments are illuminated either by an ...

Page 168: ...he ground The minimum wing tip turning radius using full steering one brake and partial power is 26 feet 10 inches WING FLAPS MANUAL The four position flaps are operated by a manual lever located between the front seats As the handle is raised to lower the flaps a definite detent and click of the thumb release button will be felt at the 15 25 and 35 flap extended positions To retract the flaps dep...

Page 169: ...b out requires no change in trim and only light changes in control forces The light forces dissipate without change in trim or significant change in airspeed CAUTION Establish recovery altitude and recovery power before retracting flaps during slow flight particularly during recoveries from approach configurations LANDING GEAR The retractable tricycle landing gear fabricated from magnesium casting...

Page 170: ...g the warning light test button on the instrument panel will verify the landing gear lamps are illuminating The intensity of the lamps can be controlled by turnin the lens holder on each lamp TIME DELAY RELAY MC 674 and after Landing gear retracti_on operation is protected by a time delay relay which will disengage electrical power to the hydraulic pump motor after 30 seconds of continuous pump op...

Page 171: ...ontinuously CIRCUIT BREAKER The landing GEAR MOTOR circuit breaker is located on the right subpanet This circuit breaker is a pull and reset type breaker A white circle identifies this circuit breaker The breaker will pop out under overload conditions The remainder of the landing gear circuitry is protected by a push to reset circuit breaker marked GEAR IND WARNING The landing gear system will be ...

Page 172: ...he control in to release the brakes CAUTION Install wheel chocks and release the parking brake if the airplane is to be left unattended Changes in ambient temperature can cause the brakes to release or to exert excessive pressures LANDING GEAR SAFETY EXTENSION SYSTEM The landing gear safety system is designed to prevent gear up landings The system is to be used as a safety device only normal usage...

Page 173: ...or less the landing gear safety system ON OFF switch must be placed in the OFF position before placing the landing gear position switch in the UP position In the event of an emergency automatic extension of the landing gear may be prevented by placing the landing gear safety system ON OFF switch in the OFF position thus deactivating the safety system BAGGAGE COMPARTMENT A 19 5 cubic foot baggage s...

Page 174: ... through the end of the buckle Holding the buckle at a right angle to the belt releases the binding action allowing the belt to slip SHOULDER HARNESSES The shoulder harness is a standard installation for all seats and should be used with the seats in the upright position The spring loading at the inertia reel keeps the harness snug but will allow normal movement during flight operations The inerti...

Page 175: ...ne has a conventional cabin door on each side of the fuselage adjacent to the forward seats When closed the outside cabin door handle is spring loaded to fit into a recess in the door The door may be locked with a key To open the door from the outside grasp the flush handle and pull until the door opens To close the cabin doors from the inside grasp the armrest attached to the door and firmly pull...

Page 176: ...exit can be accomplished through any of the three doors CONTROL LOCKS A control lock is provided with the loose tools to prevent movement of the control column and impairs access to the magneto start switch To install the Control Lock 1 Rotate control wheel and move control column so the holes in the control column hanger and the control column will align to accept the pin 2 Push the control colum...

Page 177: ... or copilot s seat A controllable friction lever located to the right of the control levers is provided to prevent creeping ENGINE INSTRUMENTS The engine instrument cluster is located on the lower left subpanel and includes the left fuel quantity indicator an ammeter oil temperature oil pressure and the right fuel quantity indicator The tachometer and manifold pressure fuel flow indicators are loc...

Page 178: ...d from 55 to 75 power The lowest value of a given sector is the lean limit setting and the highest value of the sector is the best power setting for that particular power range The take off and climb range is covered by green sectors for full power at various altitudes The full power markings represent the maximum performance mixtures for the altitudes shown permitting leaning of the mixture for m...

Page 179: ... stabilizes After the first 25 hours of operation drain and replace the mineral oil A change to an approved engine oil should be made after the break in period Refer to Lycoming Engine Operator s Manual NOTE In order to promote proper ring seating cruise power settings of 65 to 75 should be used until a total of 50 hours has accumulated or until oil consumption has stabilized This recommendation i...

Page 180: ...witch located on the subpanel to the left of the pilot s control column incorporates R right L left and BOTH magneto positions in addition to the normal OFF and START positions After activation of the starter the spring loaded switch returns to the BOTH position when released Battery switch and alternator switch are grouped on the subpanel to the right of the pilot s control column The warning lig...

Page 181: ... power quadrant allows the pilot to select the governor s rpm range Governor boosted oil pressure holds the propeller blades in a high pitch low rpm position during normal cruise operation If oil pressure is lost the propeller will go to the full high rpm low pitch position FUEL SYSTEM The airplane is designed for operation on grade 100 green or 100LL blue aviation gasoline FUEL TANKS Fuel tanks l...

Page 182: ...e desired tank through a fuel selector valve in the center floorboard and then through a strainer to the engine driven fuel pump FUEL QUANTITY INDICATORS Fuel quantity is measured by float operated sensors located in each wing tank system These transmit electrical signals to the individual indicators which indicate fuel remaining in each tank The indicating system reads full at 20 gallons FUEL DRA...

Page 183: ...he combination fuel drain emergency landing gear extension tool provided with the loose tools It is normally kept in the pocket on the pilot s door To open the drain valve insert the tab end of the tool into the opening in the center of the valve and push upward Removing the tool will close the valve This type of drain can be locked open by pushing upward with the tool and rotating counterclockwis...

Page 184: ...een 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 If the engine stops because of insufficient fuel refer to the EMERGENCY PROCEDURES Section for the Air Start procedures FUEL...

Page 185: ...the left subpanel In addition there is an in line fuse in the rotating beacon wire and in the strobe light wire forward of the left subpanel with spare fuses adjacent to the fuse holder There is also a fuse on the left side of the quadrant pedestal for the electric clock if installed or an in line fuse near the battery box BATTERY 14 VOLT SYSTEM A 12 volt battery is located in the aft fuselage Bat...

Page 186: ...itch position The alternator field circuit breaker and alternator output circuit breaker are located on the right subpanel MC 449 MC 452 through MC 642 On airplanes MC 643 through MC 673 and airplanes MC 449 MC 452 through MC 642 with installation of Beech Kit No 23 3009 1 S the alternator circuit is protected by an alternator field circuit breaker on the right subpanel and an alternator output cu...

Page 187: ...d 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 between the external power receptacle and the main bus...

Page 188: ...e map light MC 689 MC 702 and after do not have a map light installed are controlled by a rheostat switch located on the pedestal below the power quadrant EXTERIOR LIGHTING The switches 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 tip...

Page 189: ...H AUST Alt C OCICPll OUTllTS 12 1x D EXHAUST BEECHCRAFT Sierra C24R i FIi WAll flfSH All JNlU COCKPIJ HU l U OUfUTS 1 1 IH l t CAIIN HUTU ouuns 13 ia E i 1 f HESH Ala OUflUS I STAND 00 16 o uoNAll O llONAl 1 ENTllATION FAN ENVIRONMENTAL SCHEMATIC 7 32 November 1980 ...

Page 190: ...ot or cold air may enter the cabin through the firewall outlets The knob marked CABIN AIR regulates the quantity of air entering the cabin through this firewall outlet With the CABIN AIR knob in pull out the CABIN HEAT knob for heated air and push it in for fresh air There are 4 outlets for cabin heat distribution in the standard installation however 5 outlets are provided when the optional childr...

Page 191: ...n the aft cabin for flow through ventilation PITOT ANO STATIC SYSTEMS PITOT SYSTEM The pitot system provides a source of impact air for operation of the airspeed 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 element which is turned on and off with a switch on the instrument panel The switch should be ON when ...

Page 192: ...gyroscopic flight instruments and other air driven equipment is supplied by an engine driven vacuum pump An adjustable relief valve controls suction by bleeding outside air into the vacuum pump A suction gage indicates system vacuum in inches of mercury 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 o...

Page 193: ...le is factory set to sound a warning 5 to 7 mph above a stall condition and continues steadily as the airplane approaches a complete stall The stall warning horn triggered by a sensing vane on the leading edge of the left wing is equally effective in all flight configurations and at all weights 7 36 December 1982 ...

Page 194: ...I r ...

Page 195: ...hed By A Certificated 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 9 Fuel Cells 8 9 Flight Control Surfaces 8 9 Grounding 8 9 PilotTube 8 9 Windshield and Windows 8 9 During Flyable Storage 8 10 Preparation for Service 8 10 Prolonged Out of Service Care 8 10 No...

Page 196: ...em 8 17 Propeller Blades 8 17 Minor Maintenance Rubber Seals 8 18 Alternator 8 18 Magnetos 8 19 Cleaning Exterior Paint Finishes 8 19 Lacquer Paint Finishes 8 19 Urethane Paint Finishes 8 20 Windshield and Windows 8 21 Interior 8 21 Engine 8 22 Lubrication 8 22 Lubrication Points 8 23 Recommended Servicing Schedule 8 29 Consumable Materials 8 32 Approved Engine Oils 8 34 Bulb Replacement Guide 8 3...

Page 197: ...ents established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers or International Distributors or Dealers can provide recommended modification service and operating procedures issued by both the FAA and Beech Aircraft Corporation designed to...

Page 198: ...lly provided to the holder of this handbook For information on how to obtain Revision Service applicable to this handbook consult a BEECHCRAFT Aero or Aviation Center or International Distributor or Dealer or refer to the latest revision of BEECHCAAFT Service Instructions No 0250 010 AIRPLANE INSPECTION PERIODS 1 FAA Required Annual Inspections 2 BEECHCRAFT Recommended Inspection Guide 3 Continuin...

Page 199: ...ce operation 2 All 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 concerning 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 ensure that ...

Page 200: ...e 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 lower 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 tip while t...

Page 201: ...ssive pressures CONTROL COLUMN LOCK PIN 1 Rotate the control wheel and move control column so the holes in the control column hanger and the control column will align to 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 lock pin by positio...

Page 202: ...icipated a vertical tail post can be 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 scissors jack under the axle Also jack pads are installed to facilitate landing gear retraction checks Refer to the BEECHCRAFT Shop Manual for proper procedures 8 8 CAUTION The landing gear circuit breaker should b...

Page 203: ...ompress the nose gear and reduce the angle of attack of the wings Attach a line to the nose gear for additional tie down FUEL CELLS Fill to capacity to minimize fuel vapor FLIGHT CONTROL SURFACES Lock with internal and external locks GROUNDING Static ground airplane securely and effectively PITOT TUBE Install cover WINDSHIELD AND WINDOWS Close all windows and window vents It is recommended that co...

Page 204: ...he engine over five revolutions by means of the propeller This will dispel any beads of moisture that may have accumulated and spread the residual lubricating oil around the cylinder walls Unless the airplane is flown repeat this procedure every five days After 30 days the airplane should be flown for 30 minutes or a ground runup should be made long enough to produce an oil temperature within the ...

Page 205: ...ed with a 28 volt electrical system require a setting of 27 75 to 28 25 volts CAUTION On 14 volt airplanes the power pin for external power is connected directly to the battery 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 p...

Page 206: ...n alternate fuels Two 29 9 gallon fuel tanks are located in the wings just outboard of the wing root A visual measuring tab located below the tank filler neck facilitates a fuel load of 15 gallons when the fuel reaches the bottom of the tab or 20 gallons when the fuel reaches the top of the slot This partial filling of the fuel tanks allows an increase in the payload The fuel indicators on the ins...

Page 207: ...e recommendations only since the frequency 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 10...

Page 208: ...ting conditions Use engine oil as indicated in Consumable Materials in this section The engine oil sump capacity is eight 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 ...

Page 209: ...teries in the airplane is discouraged If the battery is low and needs charging and servicing it should be removed from the airplane and serviced and charged in the manner prescribed in the shop manual WARNING Always connect charging cables at the battery terminals first then to the charging unit to avoid sparks near the battery fumes since explosion could occur TIRES The airplane is equipped with ...

Page 210: ...omponent develops an external teak or a skip in the damping action it should be replaced BRAKES The brake hydraulic fluid reservoir is located on the firewall in the engine compartment Refer to Consumable Materials in this section for hydraulic fluid specification Since the pistons move to compensate for lining wear the brakes require no adjustment Complete information on brake wheel and tire main...

Page 211: ... firewall or mounted on the left instrument panel brace immediately under the glareshield PROPELLER BLADES The daily preflight inspection should include a careful examination of the propeller blades for nicks and scratches Each blade leading edge should receive particular attention It is very important that all nicks and scratches be smoothed out and polished Any BEECHCRAFT Aero or Aviation Center...

Page 212: ...n installing a battery make certain that the ground polarity of the battery and the ground polarity of the alternator are the same 2 When connecting a booster battery be sure to connect 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 ...

Page 213: ...is grounded to the engine case Otherwise all spark plug leads should be disconnected or the cable outlet plate on the rear of the magneto should be removed CLEANING EXTERIOR PAINT FINISHES In the standard configuration the BEECHCRAFT Sierra C24R is painted with a lacquer paint finish Optional urethane paint finishes are available LACQUER PAINT FINISHES Because wax seals the paint from the outside ...

Page 214: ...a thorough waxing will protect painted and unpainted metal surfaces from a variety of highly corrosive elements Flush loose dirt away first with clear water then wash the airplane with a mild soap and water Harsh abrasive or alkaline soaps or detergents should never be used Use a soft cleaning cloth or chamois to prevent scratches when cleaning and polishing Any good grade automobile wax may be us...

Page 215: ...de fire extinguisher fluid deice fluid or lacquer thinners on the windshield or windows as these substances have a tendency to soften and craze the surface INTERIOR The seats rugs upholstery panels and headliner should be vacuum cleaned frequently Do not use water to clean fabric surfaces Commercial foam type cleaners or shampoos can be used to clean rugs fabrics and upholstery however the instruc...

Page 216: ...peration is performed 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 off excess lubricant to prevent the accumulation of d...

Page 217: ... BEECHCRAFT SlerraC24R Section VIII Handling Serv Malnt LUBRICATION POINTS D C C24A 604 14 DETAIL A NOSE GEAR STEERING C24A 604 15 November 1980 8 23 ...

Page 218: ... Section VIII Handling Serv Malnt DETAIL B FLAP MECHANISM DETAIL C RUDDER BELLCRANK RUDDER HINGE 8 24 BEECHCRAFT Sierra C24R C24A 604 16 C24A 604 17 C24A 604 18 November 1980 ...

Page 219: ...raC24R Section VIII Handling Serv Malnt DETAIL E ELEVATOR HINGE C24R 604 19 DETAIL F A STABILATOR HINGE BRACKET c24R 604 2o DETAIL G AILERON BELLCRANK C24R 604 21 AIL H I RUDDER MECHANISM C24R 604 22 November 1980 8 25 ...

Page 220: ... Section VIII Handling Serv Malnt BEECHCRAFT SlerraC24R LANDING GEAR C24R 604 23 DETAIL J CENTRAL COLUMN LINKAGE C24R 604 24 DETAIL K I TRIM TAB ACTUATOR C24R 604 25 8 26 November _ 1980 ...

Page 221: ... BEECHCRAFT SlerraC24R DETAIL L Section VIII Handling Serv Malnt AILERON HINGE ANO ROD ENDS C24R 604 26 DETAIL M LANDING GEAR RESERVOIR C24R 604 27 November 1980 8 27 ...

Page 222: ...OTE NUMBERS REFER TO ITEMS IN THE CONSUMABLE MATERIALS CHART LUBRICATE ALL PLAIN BEARING BUSHINGS AS REQUIRED OR EVERY 500 HOURS WITH SAE NO 30 OIL 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 C24R 604 29 November 1980 ...

Page 223: ...anks Top of wings 3 Check battery electrolyte Behind aft cabin bulkhead See Shop Manual Clean Induction air filter In lower forward cowl Lubricate landing gear On landing gear I 5 knee pins Change engine oil Lower side of engine 1 Clean oil screens Aft right side of accessory 2 case and bottom of sump Central brake reservoir On firewall N 7 Hydraulic gear pump reservoir Aft of rear seat 7 bulkhead...

Page 224: ...cate aileron bell crank Lubricate aileron pivotal points and rod ends Replace induction air filter LOCATION Letters refer to Lubrication Points Diagram Landing gear I On top of nose gear A On aft side of nose gear A Under floorboards B Under floorboards BJ Bottom of rudder C On rudder leading edge DJ On trailing edge of stabilator E In aft tail section F In wing forward of aileron G Outboard trail...

Page 225: ...t panel J In aft tail section K In engine compartment 11 11 11 9 UJ a i rn 0 u u I z I 1 Anytime the control surfaces are altered repaired or repainted they must be a_ rebalanced per the Maintenance Manual 2 Check the wing bolts for proper torque at the first 100 hour inspection and at the first P 100 hour inspection after each reinstallation of the wing attach bolts 3 Emergency Locator Transmitte...

Page 226: ... or 100LL blue Grade 4 Lubricant Powdered MIL C 6711 Graphite t5 Grease High Low Aero Lubriplate Temperature 6 Corrosion Preven MIL C 6529 live Engine 7 Hydraulic Fluid MIL H 5606 tt8 Grease General MIL G 81322 Purpose Wide Temperature tt9 Grease High Low MIL G 23827 Temperature 10 Lubricating Oil MIL L 7870 Low Temperature 11 Lubricating Oil SAE No 20 or 1OW 30 12 Fuel Additive Alcor TCP Concentr...

Page 227: ...ight mineral type and MIL L 22851 ashless dispersant lubricants for airplane engines If grade 100 green fuel is not available use 100LL blue Mix with quick evaporating liquid naphtha and apply with a brush tProduct of BRC Bearing Company Wichita Kansas ttln extremelycold climates MIL G 23827 grease should be used in place of MIL G 81322 grease Care should be exercised when using either MIL G 81322...

Page 228: ...il and Aefinirig Co 8 34 PRODUCT IDENTIFICATION Global Concentrate A Paranox 160 and 165 AT 451 AM 173E RM 180E Shell Concentrate A Code 60068 Aeroshell W 120 Aeroshell W 80 TX 6309 Aircraft Engine Oil Premium AD120 Aircraf1 Erigine Oil Premium AD80 pa Aviation Lubricant 753 Chevron Aero Oil Grade 120 Exxon Aviation Oil E 120 Exxon Aviation Oil A 100 Exxon Aviation Oil E 80 Chevron Aero Oil Grade ...

Page 229: ...11100 Phillips 66 Aviation Engine Oil Grade 1065 Phillips 66 Aviation Engine Oil Grade 1100 Aeroshell Oil 65 Aeroshell Oil 100 NOTE A straight mineral oil conforming to MIL L 6082 may be used until the oil consumption has stabilized Vendors listed as meeting Federal and Military Specifications are provided as reference only and are not specifically recommended by Beech Aircraft Corporation Any pro...

Page 230: ...OLT Compass light 330 327 Dome light cabin 89 303 Instrument flood light 89 303 overhead Landing gear position 330 327 light Landing light wing 4313 4596 Navigation light tail 1777 1683 cone Navigation light wing 1512 1524 Rotating beacon WRM 44KA WRM 1939 or WRM 1940 Taxi light 4595 4594 8 36 November 1980 ...

Page 231: ...noted in this manual are based on average usage and average environmental conditions SPECIAL CONDITIONS CAUTIONARY NOTIC 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 the...

Page 232: ...WER PLANT NOTE On Condition On Condition On Condition On Condition On Condition On Condition On Condition On Condition On Condition When an engine has been overhauled or a new engine installed it is recommended that low power settings NOT be used until oil consumption has stabilized The average time for piston ring seating is approximately 50 hours Refer to Lycoming Engine Operator s Manual Engine...

Page 233: ...s Propeller Controls On Condition Propeller Governor At engine overhaul but not to exceed 1500 hours or 4 years Magnetos On Condition Engine Driven Fuel At Engine Overhaul or Pump On Condition Cabin Heat Muff Inspect every 100 hours Flap Position Indicator On Condition Free Air Temperature Indicator On Condition All hose Hoses carrying flammable liquids at engine overhaul or every 5 years All othe...

Page 234: ...on condition On Condition On Condition INSTRUMENTS Turn Coordinator Altimeter Directional Gyro Gyro Pressure Engine Indicator Units Airspeed Indicator Rate of Climb Indicator Fuel Quantity Indicator Manifold Pressure Fuel Flow Indicator Tachometer On Condition Every 24 months per FAA Directive On Condition On Condition On Condition On Condition On Condition On Condition On Condition On Condition E...

Page 235: ...nths re charge as necessary On Condition Inspect every 12 months INSPECTIONS The FAA requires that an airplane used for hire be inspected at each 100 hours of operation by qualified personnel Airplanes which are not used for hire are required to have an inspection by qualified personnel on an annual basis Good operating practice requires that the airplane be preflighted prior to takeoff Items foun...

Page 236: ...ude the following Operational Inspection 1 Alternator voltage regulator functioning 2 Engine instruments 3 Flight instruments 4 Idle rpm and mixture 5 Engine controls operation 6 All lights 7 Radio operation 8 Magneto check 9 Brake operation 10 Tank selector operation 11 Heat and vent system operation 12 Starter operation 13 Electrical switches and circuit breakers 14 Power check 2650 to 2700 rpm ...

Page 237: ... and gap spark plugs Cabin and Aft Fuselage 1 Flight control operation through full travel and proper direction of travel 2 Storm window and door operation 3 Check interior furnishings and seat belts 4 Check battery water level 5 Check hydraulic pump reservoir Exterior 1 Check flight control surfaces for condition and security 2 Check tires brake pucks and discs 3 Check static ports pilot mast and...

Page 238: ... ...

Page 239: ...installed 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 Approved Airplane ...

Page 240: ... Section IX Supplements BEECHCRAFT Sierra C24R INTENTIONALLY LEFT BLANK 9 2 November 1980 ...

Page 241: ...AA APPROVED AIRPLANE FLIGHT MANUAL LOG OF SUPPLEMENTS FAA Supplements must be in the airplane for flight operation when subject equipment is installed Number Subject srr ec S o 52S7 51V J avro P 1 t or Be 4 1T lht2 A 7ET2 l EC Se WJ b 67 VVfC So _5 November 1980 Rev Date No 9 3 ...

Page 242: ...nstalle in accordance with STC SA 5254SW 0 The infor mation contained herein s upplements the informa tion of the basic POH and or AFM for limitations Procedures and Performance information not contai ned in this Supp ement consult the basic POH and or AFM SECTION l GENERAL This manual is to acquaint the pi1ot with the features and func tions of the System SO T wo Axis Autopilot and to provide ope...

Page 243: ...Climb Cruise Oesctnt 55 1 20 6rf 100 600 220 The fol lowing altitude losses and bank angles were recorded after a malfunction with a I second recov ery delay Configuration Maneuvering Approach coupled or uncoupled Bank Angle Altitude Loss 15 40 25 30 The above values are t he worst case for all the models covered by this doculllent N ORMAL OPERATIIIG PROCEDURES 4 1 SYSTEM OESCRIPTIOH The Syste11 5...

Page 244: ...ion by use of the accelerometer and the pressure transducer When the altitude hold mode is engaged an elevator tri01 sensor fo the pitch servo will detect the elevator trim condit ion When elevator trim is necessary to re establish a trifmled condition trim indicator lights on the prograirmer unit will illuminate to indicate the direction to trim to restore a trinmed condition The indicator and an...

Page 245: ...ignals Reverse Approach Mode Switch REV Momentary activation will engage the reverse tracking node for use when tracking a localizer backcourse This mode provides the sarne system gain as the APR Mode with reverse needle sensing Down TRIM light OH This light llluninates to indic te the need for nose down trim When both the UP and J t _ lights are not lighted t he aircraft is in trim longitudinaITy...

Page 246: ...ust be reconducted to get a ready in dication If the ready l ight does not illuminate after the test a failure to pass the test is i ndica ted and the system will reiuire service NOTE W JlR tllRR N tonfis NGAGEO UNLESS POWE IS 011 SYSTEM FUNCTIONAL TEST 3 Depress ON OFF Switch STB Annunciator illuminates Rotate turn knob left and right observe control wheel moves in corresponding direction Center ...

Page 247: ... that roll and pitch servo release Move control wheel to confirm roll and pitch motions are free with no control restriction or bindi ng If the optional disconnect switch i s installed it may be used to effect the disconnect for this check IN FLIGHT PROCEDURES NOTE The required pre flight test can be conducted in the air if necessary It should be noted however that when the UP ON lights are flashi...

Page 248: ... back course center and when on the inbound heading select REV l ode Approoch Mode may be used to track YOR radials cross country if desired Use of APR Mode for cross country tracking nw IY result in some course scalloping if the VOR signal is weak or otherwise noisey In areas of poor siqnal quality NAV Mode may provide more accurate tracking even with reduced gain SECTION V OPERATIONAL DATA Text ...

Page 249: ...according to Bulletin No 314 Revision 1 dated 12 20 84 and Master Drawing List No 92240 Revision A dated 12 20 84 and or later FAA Approved revisions of the above data 28 Volt System J _A d f t 1 FAA Approved Supplement to Pilot I s Operating Handbook and or FAA Approved Airplane flight Manual P N 89328 dated 12 23 83 is required for Beech Model C24R for S TEC System 40 and or later FAA Approved r...

Page 250: ...proved revisions of the above supplement 3 FAA Approved Supplemental Flight Manual P N 89579 dated 3 4 85 is required for Beech odel C23 for S TEC System 40 and or later FAA Approved revisions of the above supplement 4 FAA Approved Supplemental Flight Manual P N 89580 dated 3 4 85 i s requ ired for Oeech l bdel C23 for s TEC System 50 and or later FAA Appro ed revisions of the abov e supplement 5 ...

Page 251: ...g xte iel Shunts N9Tz The e b ve models a e 2pproved es eplace lent s _f u _ fiMu 1 I C p v u Approva l of h s change in t pe design appli s t the zOove r efe enccd aircraft co iels only This 2 ppro 1al should not be ex endeC t o airc c t of this inodel on hich ot er previous cpproved codi eat ons e re ncorporz ed U lle s is det er iineci that t ie clati onship et cn this che tge and a ny of those...

Page 252: ... Approved Model List s form a part of th is certificate _t 1 a _d tf w Th is ag p rova should nor be t xtended to other a ircra t this oodel on fflich other previOuil y ipproved modifications are incorporated uni i t is detcrrDined by the installer that the interrelationship bctveen this chantt and any of those other previously ap_pr oved lbOdifications will introduce no advcr effect upon the airv...

Page 253: ...dn icc vith in s al lation instructi oris NO _ 7405 dat ed Ju 10 17 1976 O late FM approved r vision Brt 7510 Af PLICt ILITY LIST Install DA 7510 rilte Asse i bly in ac cordan viU i isi al la ion instructions No BA 7503 c ated June 7 1976 oc later FAA approved revision F AA APPROVED JUN 1 3 iSS2 r B 7610 APPLIO DILITY L tST Inst ll DA 7610 Filtcr As cm blv in accordance vith inst al 1aiion instruc...

Page 254: ...inal cquipme u instrumc ua1ion Sc rhe ccnunuanon si fo ie uir d 9iac irds t f Approval of his caange in ty e design applies to the bove aicdel airc afr onJy This approvaJ should not be extended to other aircr tft of these models on whic t orhe prc iousiy approved modificJ tions are incorporated unless it is de ermined that the re ationsh p Cerwe n this chJ nge and any ofthose orhcr prc tiousiy app...

Page 255: ...piaca rcis must be lCC ted on the mstrJmem panel adJace it to ht t l iOrucs Ime 1 1 1onli fu ow pressure nsr ume ll 2pproved by this S7C For all lrc afi mcciels DO OT RELY ON FliEL FLOWINSTRUMEYf TO DETERMINE n EL LZ VELS IN T 1_ iKS For aii ia ft origin aily equipped with fuei flow ar d or pressure nsuume its RE 1 TO ORIGi NAL Fl EL F OWIPRESSl RE INSTRljME iTATION FOR RIMr RYic FOR l o END ...

Page 256: ...n OM r I I S s l r S I t S f z 1 r S I t t S S I S I S I I z I i a 1 1 l l f l r ...

Page 257: ...ppl ies to the abOve 1lltJ l gTTT15 is approval should not be extended to engines of this r iodel t i l whi ch ottler previously approved modificati ons are incorpor ated uoless it is determined that the relationship between this chznge and any of those other previ Jusly approved modifications including changes in type design will introduce no adverse effect upcir the aiNorthiness of that engine A...

Page 258: ...e Cert ificate Oata Sheet apply except a s noted herein NOTE The following placard is mandatory on aircraft that are required to have POH AFH s and must be located near instrun ent suction gauge in full view of pilot I STANDBY VACUUM SYSTEM I ffOR OPERATING INSTRUCTIONS AND LIMITATIONS SEE SUPPLEMENT IIN OWNER S MANUAL DR PILOT S OPERATING HANDBOOK t ______ _____ _ _ _ ___ __ ________ _ __________...

Page 259: ...El779 1 1 PREC S ft IGHT ST li NOBY VACUUM SYSTS t LIST OF CTIVE p_ 1 Gt S PAGE AMENDMENT DATE FAA Approved c _ f_ ssistant Mariager Seattle Aircraft Certification Of ice Amended Septefflber 9 1990 08 22 90 12 28 82 1 2 28 82 ...

Page 260: ...I E 229 CAR ll ond T C E 223 LYC SVS t I I I QO I I E 274 C IR U on l T C E 21 LYC SVS l l 001 1 l 1 I I l I 12 CAA l3 Md T C E12 L YC SVS r J oo1 E 277 l CAA 13 end T C E 277 LYC 5VS i i 1 oon 1 1 0 I I iD l50 217 i CAAUondT C 217 LYC 5 15 i l oon I l o J60 LO J60 E 286 r ARUoodT c E 286 LYc svs l I I0 360 t l 00 I l ll0 3 0 1 J I 1 l l t 1 I I I I 8 A IQ JGO EU l CAR 13 aod T c ft LYC SYS j I 00...

Page 261: ... change in type de sign applies to the basic eech Models u listed on the ttached MEL This 1pproval 1 4 t tf ui t u should not be extended to afrcuft o this n det on vhich other previousl y approved modifications are incorporated unless it is decuinined t hat the relationship bctvcen this change a nd any of thou otbe r p re viously approved odific a t ions including changes in type design vill intr...

Page 262: ...IFIED BY STC Equipment The Airplane Flight Hanual or Pilot I s Operating handbook Supplu1cnc must be l lAintiancd in the ait planc at all times NOTE 1 Current eight and balance r eport including lisc of equipce nt in the ce tificd eapty veizhc must be in the aircnft NO 2 In addition to the Placards and Markings r equired by Type Ce rtificate Dae a Sheets Note 2 apply the follouing One of the follo...

Page 263: ...hm SA2 60SM SUPPLEHE l TAL TYPE CERTIFICA TE ADDC NDUH NO SA2160NM APPROX PRESS ALT STANDH VACUUM AVAILASLE ALTITUDE POl ER CHART I FOR AIRCRAFT W lTH FIXED PITCH PRO PELLER I I I SYS VACUUM J RPM IN HG HIN I I 2000 4000 6000 e_ _ 1 _ _ _ _ _ _ l _ _ _ _ _ _ _ _ _ _ _ I 8000 10000 T 6 t tr ti J j 1 uf ruJ w l i F fR 11 1 P AGe 4 0 4 l ACiCS ...

Page 264: ...ot s Ope r a t ing Hendbook i s applic able and ir 1 1 st b carried in the basic h ti ndboo k ihttn th airplt ne i modi fied by the instc 11lation ot a PRECISE FLIGHT STANDBY VACU1JM SYSTEM a s specified in the Uppleme ntal Type Certificate N lmber listed abov The information in this docUment s upersedes the b asi c hand book only wherE covered in items contained i n this supplement For 1i mitatio...

Page 265: ...f vacuum Vacuum powered or vacuum gyro d irected auto pilot should be OFF when op e r ati ng with failed primary vacuum syste m 3 The SVS is not designed to opel ated pneumatic de ice systems 00 NOl opera te this typo de ice system when operat ing with a failed pr ima1 y v accum system 4 Above 10 000 feet pressure altitude engine powe r setti ngs may have to b e significantly reduced t o provide a...

Page 266: ...ato r af ter appropr i ate entries have b een made Approx imate Stand by Vac uum Av91ilab le Al titude Povier Ch art t or Airc raf t 1 Jith c s Prop Ma x Cont r PH P ress Man SV Vac uum Alt RPM Press I n Hg Min A M Max r_ nr 4 AAA Max 6000 M x c n Mall ont 1 Ql I H x c nr Aproximat e St andby Vac uum Availabl e Alti ude Power Chart for Aircraft wi t h Fixed Pitch Prop Press svs Vac uum Alt RPM In ...

Page 267: ...FR CONOITION OR LANDING 3 If descent is i npracticable a Periodically reduce power as r equired to Spool up the gyros b Reapply power as required while comparing vacuum dr iven gyros against the tuYn and bank turn coordinator VSI and other f 1i ght instruments c When an obvious discTepancy is noted between the vacuu n driven instrument and the other flight instrument REPEAT the above spool up proc...

Page 268: ...AA APPROVED MODEL LIST NO SA 21G0NM PRECISE FLIGIIT SVS l IST OF ACTIVE PAGES AMENDMEN l DA rE 2 4 RS FAA APPROVED Speci al Certification Orancll Seattle JrcrJft CertiJjcati on Office AMENDMENT DATE PAGE l OF 3 ...

Page 269: ...H SUPPLEMENT AMENO F NT ITEM MAKI MOl l t N UMBER ALTERA1 I ON INSTRUCTIONS NUMDER DA1 E UATt I HEl CH 2J A23 A23A AlCE CAR PAR1 3 SVS l I I 12 7 84 AlllCRAl T A23 L0 19A COKP 8l9 M19A A23 24 823 C23 A2 4 B 24R l 35 AJS D35 777 CAR PART 03 SVS l 11 12 7 84 C35 D3S E35 F35 G35 35R 1135 J35 K35 3AJ 5 CAR PART 3 SVS 111 12 7 84 M3S N351 P35 I S35 V35 V35A VJSB 35 33 35 AJl 35 B33 35 CJJ 35 C33A E33 E...

Page 270: ...and SL7 3857 Pl O oil control ring in accorda ncewith Superior 1 ir Parts Inc procedure tor gringing high coinprcssion Nitrided cylinder barralc i a nd installation ot 5 0 f io t e8 a o ciM Co z patibility ot this t iodi ication ith proviou zl y installed cquip iont rJ ust be dete n ined by installer ii _q J __ d _ L d k l P _ l 4 u a 7d dl ugust 15 1988 April ll 1989 ju ju il y d l Y m u _4 e _ _...

Page 271: ...AlD AlE A2D LI0 360 ClE ClEG ClE60 HI0 360 AlA ClA ClB LHI0 360 Cl Type Cert ficate uunb r E ns 1 0 G0 480 ClB6 C1D6 C2 SERIES G206 G2F6 Gl11 6 GlAG HELIO GlBG Gl06 HELIO Gl06 GlE6 GlF6 G1G6 GlJ 6 IG0 4 80 AlB5 HELIO Tvpe c rtificatP Nurn ber 1E4 11 I0 540 MlAS ElBS AlA GlAS GlBS GlCS Gl DS GlE5 KlAS KlBS KlOS KlFS LlAS D111 5 BlCS Ell 5 ElBS GlF5 KlCS KlES PlAS Sll 5 1 Kll 50 KlFSD KlGS KlGSD KlH...

Page 272: ...document must be carried in the airplane al all limes when the Gannin GNS unit is installed in accon lunce with STC SAO I933LA D This documc nt must be incorporated into lhc FAA Approved Airplane flight Manual or provided as an FAA Approved Supplcmentul Airplane Flight Manual Th information contained herein supplements the infonnution in the FAA Approved Airplane Flight Manual For limitation proce...

Page 273: ...added LP approach type ODA STC Unit Administrator ODA 240087 CE Garmin International Inc 03 21 13 Complete Rewrite Michael Warren ODA STC Unit Administrator ODA 240087 CE Gamiin lntc marional Inc 01 27 14 Added LP V approach type Michael warren ODA STC Unit Administrator ODA 240087 CE Garmin International Inc I1 20 2014 Updated SecPage I document revisions and added Right Stream 210 Added note for...

Page 274: ... Crossfill 2 13 Flight Stream210 Optional Section 3 EMERGENCY PROCEDURES 3 I Emergency Procedures 3 2 Abnormal Procedures Section 4 NORMAL PROCEDURES 4 1 t nit Power On 4 2 Before Takeoff 4 3 HSI and EHSI Operation 4 4 Autopilot Operation 4 5 Coupling the Autopilot during approaches 4 6 Traffic Mode Selection Optional Section 5 PERFORMANCE Section 6 WEIGHT AND BAIANCE Section 7 SYSTEM DESCRIPTIONS...

Page 275: ...phical menus which are controlled by the buttons and the dual concentric rotary knob along the bottom and right side ofthe display Optional VHF Com and VHF Nav radio functions are controlled via dedicated buttons and knobs on the left side ofthe display and adjacent to frequencies they are controlling laroe Knoo ComMOC Freq MHi C mmFreq Alp Flop Small Knob Com V OC Froq kHz Pl IO OceH forAulo Olmm...

Page 276: ...em The Garmin GNSS navigation system complies with the equipment requirements ofAC 90 105 and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF radius to fix legs Part 91 subpart K 121 125 129 and 135 operators require operational approval from the FAA The Garmin GNSS navigation system complie...

Page 277: ...with JAA Administrative Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No IO JAA TGL 10 Rev I The GNSS navigation system has one or more TSO Cl 46a Class 3 approved Garmin GNS Navigation Systems The Garmin GNSS navigation system complies with the accuracy integrity and continuity of function and contains the minimum system functions required for B RNAV operations ...

Page 278: ...ries Optional Displays PIN I90 00356 30 Rev L The Pilot s Guide Addendum pan number and revision listed below or later applicable revision must be immediately available for the flight crew whenever one or more of the following units are installed and utilized with the 4XXW Series unit Stormscope Lightning Detection System Skywatch Traffic Advisory System Bendix King Traffic Advisory System Avidyne...

Page 279: ...strument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the navigation database Discrepancies that invalidate a procedure should be reported to Garmin International The affected procedure is prohlbited from being flown using data from the navigation database until a new navigation database is installed in the aircraft and verified that the...

Page 280: ...ofRAIM ofmore than five minutes for any part ofthe intended route offlight the flight shall be delayed canceled or rerouted on a track where RAIM requirements can be met The flight may also be re planned using non GPS based navigational capabilities Forflight plaruting purposes for operations within European B RNAV R i IAV 5 and P RNAV airspace if more than one satellite is scheduled to be outof s...

Page 281: ...vice utilizing the Flight Stream 210 all waypoints and flight plan information must be verified by the erew It is not acceptable to flight plan a required alternate airport based on RNAV GPS LP LPV or LNAVNNAV approach minimums The required alternate airport must be flight planned using an LNAV approach minimums or available ground based approach aid Navigation information is referenced to the WGS...

Page 282: ...stem flight plan by its name Users are prohibited from flying any approach patlt tltat contains manually entered waypoints FR approaches are prolubited wheneverany physical or visual obstruction such as a throw over yoke restricts pilot view or access to the GNS and or the CDI 2 7 Autopilot Coupling FR installations ofa Garmin 4XXW Series unit allow the operator to fly all phases offlight based on...

Page 283: ...er information shown by the data link weather product may be significantly older than the indicated weather product age Do not rely solely upon data link services to provide Temporary Flight Restriction TFR or Notice to Airmen NOTAM information Not all TFRs and NOTAMS can be depicted on the GNS 2 11 Tr affic Display Optional Traffic may be displayed on the GNS when connected to an approved optiona...

Page 284: ...elieve the operator from complying with the requirements of 91 23 or any otheroperational regulation regarding portable electronic devices AFMS Garmin GNS 4XXW GPS SBAS System FAA APPROVED I90 00356 03 Rev E Page 13 of21 ...

Page 285: ...e to be displayed with an amber ownship icon Course guidance will be removed on the CDL Aircraft position will be based upon the last valid GPS position then estimated by Dead Reckoning methods Changes in true airspeed altirude beading or winds aloft can aff ect the estimated position substantially Dead Reckoning is only available in Enroute and Oceanic modes Terminal and Approach modes do not sup...

Page 286: ...bed below During a GPS approach in which GPS accuracy requirements cannot be met by the GPS receiver for any GPS approach type the GNS v u flag all CDI guidance and display a system message ABORT APPROACH Loss of Navigation Immediately upon viewing the message the unit wilJ revert to Terminal navigation mode alarm limits Ifthe position integrity is within tl1ese limits lateral guidance will be res...

Page 287: ...at the expense ofbasic instrument flying in IMC and basic see and avoid in VMC Pilot workload will be higher forpilots with limited familiarity in using the unit in an IFR environment particularly without the autopilot engaged Garmin provides training tools with the Pilot s Guide and PC based simulator Pilots should take full advantage of these training tools to enhance system familiariz ation 4 1...

Page 288: ...ight plan leg The pilot must verify proper course selection each time the CDI source is changed from GPS to VLOC 4 4 Autopilot Operation The GNS may be coupled to an optional autopilot ifinstalled in the aircraft when operating as prescnoed in the LIMITATIONS section oftl1is manual Autopilots coupled to the Gl S system in an analog NAV mode will follow GPS or VHF navigation guidance as they would ...

Page 289: ...n PRESS Enable A P APR Outputs SELECT ENT Button PRESS Ifcoupled Autopilot will revert to ROL mode at this time Autopilot E GAGEAPPROACH MODE D Th is installation supports coupling to the autopilot in approach mode once vertical guidance is available To couple an approach Once established on the final approach course with the final approach fix as the active waypoint the Gl S will enable vertical ...

Page 290: ... enter exit the traffic device menu It is important to note that while the traffic device menu is active the current state of the traffic system is not displayed The state of the traffic device is only displayed once the traffic device menu is exited Section 5 PERFORMANCE No change Section 6 WEIGHT AND BALANCE See current weight and balance data AFMS Garmin GNS 4XXW GPS SBAS System FAA A PPROVED 1...

Page 291: ...provides no guidance Guidance may be available on the GTN but not on the GNS in these cases The GNS will sequence the procedure as it normally would ifCrossfill were not active Once a leg type is reached that is supported on both tl1e GTN and GNS systems the systems will automatically sync to the same leg Ifthe GNS is interfaced with a GTN and tlie GTN Crossfill feature isenabled on the GNS then a...

Page 292: ...GNS For details on the operation and features ofthe Flight Stream 2 lO please refer to the GNS 400W 500W Series Optional Displays PIN 190 00356 30 Rev J For additional details about the Garmin supported devices and apps for use with the Flight Stream 210 please visit http garmin com connext supported_devices AFMS Garmin GNS 4XXW GPS SBAS System 90 00356 03 Rev E Page 2 1 of21 ...

Page 293: ...cate Si 02019Sl D lor the in tallulion und opcrntion or the hnnin Gl N 625 635 650 725 ff 750 GPS SI3AS Nal iguti n Sysll m This document must be incorpt ruteJ intn the FJ t Apprn ed Airplane rlight Manual or Jnl idcc l as nn l A ppr vi J Supplc111cntJI Airplane Pliµ ht l fanual The information contained herein supplements the inliirmation in the 1 1 1 ppron d Airplane l light i lanual For limitat...

Page 294: ...ator Added capabilities Garmin International Inc checkboxes ODA 240087 CE Added GPS Date 12 1112012 approaches without vertical Added reference to EASA AMC 20 4 Section 1 3 Removed suggestion for secondary charts Changed to Type B Software in accordance with AC 120 768 Section 1 4 Added ADS B AEG FIS B NOTAM TFR Section 2 2 Removed VFR only limitation Section 2 3 Clarified secondary navigation sou...

Page 295: ...ction 4 4 27 Added caution statement 29 Section 4 6 New section 31 Section 7 7 Added TCAD and GDL 88 as optional traffic systems 32 Section 7 8 Modified Heading Not Available operation 34 35 Sectlons 7 12 7 16 New sections 3 03 26 13 20 Section 2 17 Modified limitation 4 I 1 24 14 7 Table I Added new fW1ctions I I Section 1 4 AFMS Garmin GTN GPS SBAS System FAA APPROVED FAA Approved Michael Warren...

Page 296: ...21 Modified limitation Section 2 22 2 23 Added limitations Section 3 2 IO Added Flight Stream 210 to procedure Section 4 1 Removed telephone audio deactivation procedure Section 7 5 Added wire obstacles Section 7 9 Added Flight Stream 210 Section 7 10 Added wire obstacles Section 7 17 Added section All Sections See Page i Reformatted and updated sections to better coincide with the VFR AFMS Sectio...

Page 297: ...dded autopilot capability assessment regarding RF legs Updated installer descriptions of configuration checkboxes Added Search and Rescue autopilot note Added RNP 1 0 installation options Section 7 Added GMA 35c information Removed references to GDL88 and replaced with generic AOS B AddedGWX70 turbulence detection I note Added GTN crossfill information AFMS Garmin GTN GPS SBAS System FAA APPROVED ...

Page 298: ... 13 2 13 Autopilot Coupling 13 2 14 Terrain Proximity Function All Units 14 2 15 TAWS Function Optional 14 2 16 Polar Operations 14 2 17 Datalinked Weather Display Optional 15 2 18 Traffic Display Optional 15 2 19 StormScope Display Optional 15 2 20 Flight Planner Calculator Functions 16 2 21 Fuel Range Rings 16 Glove Use Covered Fingers 16 _3 Demo Mode 16 2 24 Active Weather Radar 16 2 25 Telepho...

Page 299: ...A 35 35c Audio Panel Optional 30 7 7 Traffic System Optional 30 7 8 StormScope Optional 31 7 9 Power 31 7 10 Databases and Flight Plan Waypoints Procedures 32 7 11 External Switches 33 7 12 7 12 Airspace Depiction and Alerts 33 7 13 Garmin ADS B Traffic System Interface Optional 34 7 14 GWX 70 Weather Radar Optional 7 15 Charts Optional 7 16 Transponder Control Optional 7 17 Telephone Audio Option...

Page 300: ...luding topographic terrain aviation and X X X X X geopolitical data Display of datalink weather products SiriusXM FIS B X X X X X Connext all ootionall Control and display of airborne weather radar optional X X Display of terminal procedures data optional X X Disolav of traffic data includinq ADS 8 optional X X X X X Display of StormScope data optional X X X X X Disolav of marker beacon annunciato...

Page 301: ...n Otf A 1d Ftr ri C tro Xpdr Pane ConrT i SD Card L rk n9 5Gt t Hint l Hm ii rJ Srnaj Knob Figure I GTN 750 Control and Display Layout 101um S JU lf On Funct r1 O f JndNat JD On Off Kf f SD Card rdes aar i r1 r uno5t on to kinc 5U lA 4c r1i t omfN rv S1andb1 o Nat Chat it I h el FK Xodr P flf t tc rrols HO WK 1 y Ph ito Sens r Larf o d Srn f ivl D Figure 2 GTN 635 650 Control and Display Layout 19...

Page 302: ...ion approach operations including those approaches titled GPS or GPS and RNAV GPS approaches The Garmin GNSS navigation system is composed ofthe GTN navigator and antenna and is approved for approach procedures with vertical guidance including LPV and LNAV VNAV and without vertical guidance including LP and LNAV within the U S National Airspace System The Garmin GNSS navigation system complies wit...

Page 303: ...ordance with JAA Administrative Guidance Material Section One General Part 3 Temporary Guidance Leaflets Leaflet No 10 JAA TGL 10 Rev 1 The GNSS navigation system consists ofone or more TSO Cl46c Class 3 approved Garmin GTN Navigation Systems The Garmin GNSS navigation system complies with the accuracy integrity and continuity offunction and contains the minimum system functions required for B RNA...

Page 304: ...describes the six Advanced RNP capabilities and the GTN capabilities Advanced RNP Feature RF legs Parallel offsets Scalable RNP RNAV holding Fixed radius transitions Time ofarrival control TOAC AFMS Garmin GTN GPS SBAS System FAA APPROVED GTN Capability Available if enabled for installation See Section 2 12 for limitations Available GTN provides CDI scalability in compliance with TSO Cl46c RNP sca...

Page 305: ...ng operators from obtaining their own operational approval for the checklist function Definitions ne following terminology is used within this document ADF ADS B AEG APR CDT DME EFB EHSI FIS B GNSS GPS GPSS GTN HOT HSI IAP IFR ILS IMC LDA LNAV Automatic Direction Finder Automatic Dependent Surveillance Broadcast Aircraft Evaluation Group FAA Approach Course Deviation Indicator Distance Measuring E...

Page 306: ...SP TACAN TAS TAWS TCAS TFR TIS VHF VFR VLOC VMC VOR WAAS WFDE XFR Area Navigation Required Navigational Performance Search and Rescue Satellite Based Augmentation System Secure Digital Simplified Directional Facility Suspend Tactical Air Navigation System Traffic Awareness System Terrain Awareness and Warning System Traffic Collision Avoidance System Temporary Flight Restriction Traffic Informatio...

Page 307: ...nt Number Required for installed IFR External HSUCDUEHSI 1or more I External GPS Annunciator See Note l l Table 2 Required Equipment Note I Certain installations require an external GPS annunciator panel If installed this annunciator must be fully functional to use the GTN GPS navigation for FR operations Single engine piston aircraft under 6 000 lbs maximum takeoff weight Required Equipment for F...

Page 308: ...of GPS RAIM shall be confirmed for the intended route of flight In the event of a predicted continuous loss ofRAIM ofmore than five minutes for any part ofthe intended route offlight the flight shall be delayed canceled or rerouted on a track where RATM requirements can be met The flight may also be re planned using non GPS based navigational capabilities For flight planning purposes for operation...

Page 309: ...lly Selecting and inserting individual named fixes from the tabase is permitted provided all fixes along the published route to be flown are inserted Manual entry ofwaypoints using latitude longitude or place bearing is prohibited It is not acceptable to flight plan a required alternate airport based on RNAV GPS LP LPV or LNAV VNAV approach minimums The required alternate airport must be flight pl...

Page 310: ...navigation is prohibited unless the flight crew verifies and uses a valid compatible and current navigation database or verifies each waypoint for accuracy by reference to current approved data GPS or GPS and R t lAV GPS instrument approaches using the Garmin navigation system are prohibited unless the flight crew verifies and uses the current navigation database GPS based instrument approaches mu...

Page 311: ... the missed approach point ofan ILS LOC LOC BC LDA SDF MLS VOR TACAN approach or any other type ofapproach not approved for GPS is not authorized with GPS navigation guidance GPS guidance can only be used for approach procedures with GPS or RNAV in the procedure title When using the Garmin VOR LOC GS receivers to fly the final approach segment VOR LOC GS navigation data must be selected and presen...

Page 312: ...waypoint must be displayed in the pilot s primary field of view 2 13 Autopilot Coupling The flight crew may fly all phases offlight based on the navigation information presented to the flight crew however not all modes may be coupled to the autopilot All autopilots may be coupled in Oceanic OCN Enroute ENR and Terminal TERM modes This installation is limited to Lateral coupling only for OPS approa...

Page 313: ...E Terrain and TAWS are separate features and mutually exclusive If TAWS B is shown on the bottom right of the dedicated terrain page then TAWS is installed 2 15 TAWS Function Optional Flight crews are authorized to deviate from their current ATC clearance to the extent necessary to comply with TAWS warnings Navigation must not be predicated upon the use ofTAWS TAWS shall be inhibited when landing ...

Page 314: ...d the text weather source All text weather displayed on the GTN also includes the raw weather text for pilot review 2 18 Traffic Display Optional Traffic may be displayed on the GTN when connected to an approved optional TCAS I TAS TIS or ADS B traffic device These systems are capable of providing traffic monitoring and alerting to the flight crew Traffic shown on the display may or may not have t...

Page 315: ...45 minutes by default The reserve value can be changed om the GTN map setup menu Fuel range data is derived by the interfaced fuel totalizer data Data entered in the Fuel Planning pages will not update the fuel range ring 2 22 Glove Use Covered Fingers No device may be used to cover fingers used to operate the GTN unless the Glove Qualification Procedure located in the Pilot s Guide Cockpit Refere...

Page 316: ...activated This option is found in the Intercom Setup Menu _ when a Garmin GMA 35 audio panel is installed 2 27 Wire Obstacle Database Only the Obstacle HOT Line database may be used Use of the Obstacle Wire database is prohibited The database version can be viewed on the start up database verification or System System Status pages 2 28 Portable Electronic Devices This STC does not relieve the oper...

Page 317: ...NOTE Only vertical maneuvers are recommended unless either operating in visual meteorological conditions VMC or the flight crew determines based on all available information that turning in addition to the vertical escape maneuver is the safest course of action or both NOTE TAWS annunciators external to the GTN may not indicate the exact threat causing the alert Example WIRE alerts may be annuncia...

Page 318: ...ted by Dead Reckoning methods Changes in true airspeed altitude heading or winds aloft can affect the estimated position substantially Dead Reckoning is only available in Enroute and Oceanic modes Terminal and Approach modes do not support Dead Reckoning If Alternate Navigation Sources ILS LOC VOR DME ADF Are Available Navigation USE ALTERNATE SOURCES IfNo Alternate Navigation Sources Are Availabl...

Page 319: ... ofnavigation must be utilized 2 3 LOSS OF COM RADIO TUNING FUNCTIONS Ifalternate COM is available Communications USE ALTERNATE COM If no alternate COM is available COM RMT XFR key if installed PRESS AND HOLD FOR 2 SECONDS NOTE This procedure will tune the active COM radio the emergency frequency 121 5 regardless ofwhat frequency is displayed on the GTN Certain failures of the tuning system wi11 a...

Page 320: ...yed the system will no longer provide TAWS alerting or display relative terrain and obstacle elevations The crew must maintain compliance with procedures that ensure minimum terrain and obstacle separation 3 2 8 DATA SOURCE HEADING SOURCE INOPERATIVE OR CONNECTION TO GTN LOST MESSAGE Without a heading source to the GTN the following features will not operate Roll steering will not be provided to t...

Page 321: ...uencing of legs requiring an altitude source The flight crew must manually sequence altitude legs as prompted by the system 10 UNRECOVERABLE LOSS OF ALL ELECTRICAL GENERATORS OR ALTERNATORS Remove power from all equipment which is not necessary for flight including GTN 2 NAV GPS 2 COM 2 and the Flight Stream 210 BT LINK if installed 190 01007 A2 Rev 5 Page 22 AFMS Garmin GTN GPS SBAS System FAA AP...

Page 322: ...g in IMC and basic see and avoid in VMC Garmin provides training tools with the Pilot s Guide and PC based simulator Pilots should take full advantage ofthese training tools to enhance system familiarization 4 1 Unit Power On Database REVIEW EFFECTIVE DATES SelfTest VERIFY OUTPUTS TO NAV INDICATORS SelfTest TAWS Remote Annunciator PULL UP ILLUMINATED TERR ILLUMINATED TERR N A ILLUMINATED TERR INHB...

Page 323: ...oupled to the GTN system in an analog NAV mode will follow GPS or VHF navigation guidance as they would with existing VOR receivers Autopilots that support GPSS or GPS Roll Steering in addition to the analog course guidance will lead course changes fly arcing procedures procedure turns and holding patterns ifcoupled in a roll steering mode The GTN supports autopilot roll steering for heading legs ...

Page 324: ... the autopilot in APR mode To couple an approach Once established on the final approach course with the final approach fix as the active waypoint the GTN will issue a flashing message indication Flashing Message Button PRESS Enable APR Output Button PRESS If coupled Autopilot will revert to ROL mode at this time Autopilot ENGAGE APPROACH MODE D This installation supports coupling to the autopilot ...

Page 325: ... navigation up to RNP 1 0 This installation does not support RF leg navigation 4 6 Coupling the Autopilot during Search and Rescue SAR Operations rch and Rescue SAR patterns created in the GTN flight plan may include ns that cannot be accomplished with standard autopilot turn rates Monitor autopilot performance relative to the desired path if coupled when using Search and Rescue patterns 190 01007...

Page 326: ...Section 5 PERFORMANCE No change Section 6 WEIGHT AND BALANCE See current weight and balance data AFMS Garmin GTN GPS SBAS System FAA APPROVED 90 01007 A2 Rev 5 Page 27 ...

Page 327: ...ally sequence the leg once the altitude rescribed in the procedure is reached D This installation has a barometric corrected altitude source The GTN will automatically sequence altitude legs This installation does not have a barometric corrected altitude source The flight crew will be prompted to manually sequence altitude legs 7 3 Auto ILS CDI Capture Auto ILS CDI Capture will not automatically s...

Page 328: ...he dedicated terrain page or main map overlay is depicted in the following manner Terrain more than 1 000 feet below the aircraft is not depicted or depicted as black Terrain between 1 000 feet and I00 feet below the aircraft is depicted as amber Terrain within 100 feet below the aircraft or above the aircraft is depicted as red Obstacles and wires on the dedicated terrain page or main map are dep...

Page 329: ...ty can be accessed from the associated stem Connext Setup page GMA 35c Only Volume controls for the audio dnel are accessed by pressing the Intercom button on the GTN display screen Aircraft alerting audio may be routed through the GMA 35 35c audio panel There are no pilot controls for alert audio volumes In the event of a loss of GMA35 3Sc function alert audio routed through the audio panel may n...

Page 330: ...lable mode Ifthe GTN system is not receiving valid heading information either because a compatible heading system is not installed or the interfaced heading system has malfunctioned the StormScopeQ page will continue to operate without a heading source and indicate HDG NIA in the upper eight corner ofthe GTN display In this mode information provided by the StormScope system is displayed relative t...

Page 331: ...the Obstacle HOT Line wire database may be used in accordance with the imitation found in Section 2 27 ia stored flight plan contains a waypoint or procedure that does not correspond to a waypoint or procedure in the navigation database in use the waypoint or procedure will become locked depicted as lockd in the flight plan Flight plans with locked waypoints may be placed in the active flight plan...

Page 332: ...N annunciator bar indicates which is active Push OBS button to chane e OBS or SUSP mode OBS SUSP Performs an OBS or SUSP function TERRINHB Toggles the TA VS Inhibit function on off This switch is part ofan external annunciator panel The terrain display is still presented ifTA VS is Inhibited Table 4 External Switches 7 12 7 12 Airspace Depiction and Alerts The GTN aides the flight crew in avoiding...

Page 333: ... pointed A green relative motion vector pointed towards your ownship indicates that the traffic target is converging on your aircraft If more than one target is occupying the same area ofthe screen the GTN will combine the two or more traffic targets into one traffic group The presence of an asterisk to the left ofa target indicates that traffic has been grouped The highest priority traffic target...

Page 334: ...splayed below an overlaid procedure chart When airborne weather radar is overlaid on the main map page the radar data is displayed above an overlaid procedure chart 7 16 Transponder Control Optional The GTN can be interfaced to a Garmin transponder for control and display of squawk code mode and additional transponder functions The activation ofthe Enable ES button on the transponder page does not...

Page 335: ... may be configured to depict point obstacles and wire obstacles at various zoom scales by the pilot by using the Map page menu The obstacle or wire overlay icon see Figure 4 will be shown near the bottom ofthe display when the obstacle or wire overlay is active based on the current zoom scale and setting selected by the pilot The settings chosen by the pilot on the Map page menu including obstacle...

Page 336: ...the Flight Stream to the PED The PED is capable ofsending flight plans to the Flight Stream which will then be available on the GTN Garmin provides a list of tested and compatible devices that can be used with the Flight Stream Connection to the Flight Stream may be possible with devices other than those on the supported device list but Bluetooth stability and wireless data integrity cannot be gua...

Page 337: ...GTN power cycles Visibility of the fuel range ring may be affected by the underlying map data selectable by the pilot The pilot may make changes to the topographic or terrain data in order or more clearly observe the fuel range ring at any time FueI range data is derived from the interfaced fuel totalizer data Data entered in the Fuel Planning pages will not update the fuel range ring 1 User Defin...

Page 338: ... Alerts Missed Approach Popups Altitude Leg Popups Heading Date Time Conventions CDI Scale The following items are crossfilled only when the GTNs are set to CROSSFILL ON User Holds Approaches Flight Plan Changes Direct To Selected OBS Course Changes Additionally the following unit changes will crossfill Temperature NAV Angle User 0 T or Magnetic Fuel 7 24 Direct To Operations When conducting Direc...

Page 339: ...is installed in accordance with Supplemental Type Certificate SAOI 714WI This document must be incorporated into the FAA Approved Airplane Flight Manual or provided as an FAA Approved Supplemental Airplane Flight Manual The information contained herein supplements the FAA approved Airplane Flight Manual For limitations procedures loading and performance information not contained in this document r...

Page 340: ...OG OF REVISIONS Number Description FAA Approved All Complete Supplement fk 1 Robert Murray ODASTCUmt Administrator Garmin lntemat1onal Inc ODA 240087 CE Date 05 _01 _201 J All New supplement format See cover page with GTX 3X5 added AFMS Garmin GTX 33X and 3X5 XPDR with ADS B FAA APPROVED ...

Page 341: ...oadcast Inhibit PABJ 13 _ 2 6 Datalinked Weather Display GTX 345 Only 13 2 7 Portable Electronic Devices 13 Section 3 EMERGENCY PROCEDURES 14 3 1 Emergency Procedures 14 3 2 Abnormal Procedures 14 Section 4 NORMAL PROCEDURES 16 4 1 Unit Power On 16 4 2 Before Takeoff 17 Section 5 PERFORMANCE 17 Section 6 WEIGHT AND BA LANCE 17 Section 7 SYSTEM DESCRIPTIOl i 18 7 1 GTX TIS Behavior 18 7 2 GTX 345R ...

Page 342: ...ded response of pulses to ground based radar on a frequency of 1090 MHz Each unit is equipped with IDENT capability and will reply to ATCRBS Mode A Mode C and Mode S All Call interrogation Interfaces to the GTX 33X are shO TI in the following block diagrams Qptio n l lntorfaces Audio Panel GTX3300 lnstalts only RequiredInterfaces Top Anllnl 2 BottomAntenn 1 GPS Heading Sourca 1 tl Traffic System G...

Page 343: ... 1090 MHz o Integration of data from internal and external sources to transmit the following data per 14 CFR 91 227 GPS Position Altitude and Position Integrity Ground Track and or Heading Ground Speed and Velocity Integrity Air Ground Status Flight ID Call Sign ICAO Registration Number Capability and Status Information Transponder Squawk Code DENT and Emergency Status o Pressure Altitude Broadcas...

Page 344: ...35R 335R 345 345 w 345R 345R GPS wGPS GPS w GPS Panel mount X X X X Remote mount X X X X ModeS X X X X X X X X ADS B out X X X X X X X X ADS B Traffic X X X X FIS B X X X X Internal GPS X X X X Bluetooth X X X X Optional Garmin Altitude X X X X X X X X Encoder Table 1 GTX 3XS Unit Configurations Interfaces to the GTX 3X5 are shown in Figure 3 l90 00734 1S Rev 2 Page 6 of 18 AFMS Garmin GTX 33X and...

Page 345: ...ission of ADS B out data on 1090 extended squitter 1090ES 1090 MHz o Integration of data from internal and external sources to transmit the following data per 14 CFR 91 227 GPS Position Altitude and Position Integrity Ground Track and or Heading Ground Speed and Velocity Integrity Air Ground Status Flight ID Call Sign ICAO Registration Number Capability and Status Information Transponder Squawk Co...

Page 346: ...a ground station Provide ADS B traffic information and alerting to the pilot via an interfaced display o Correlation and consolidation of traffic data from multiple traffic sources o Aural and visual traffic alerting Provide FIS B data to the pilot via an interfaced display o Graphical and textual weather products NEXRAD PIREPs AIRMET SIGMETs METARs TAFs Winds Aloft o Aviation Data 1 3 Capabilitie...

Page 347: ...5 GTX345R GTX 345R Interfaced GPS SBAS Position Sourcc s Internal GTN 6XX 7XX Series GNS 400W 500W Series GNS 480 GIA 63 GDL 88 GTX 330 only Interfaced Pressure Altitude Source Pressure Altitude Source I D Garmin Altitude Encoder GPS 2 if installed Internal GTN 6XX 7XX Series GNS 400W 500W Series GNS 480 GIA 63 D GDL 88 GTX 330 only Pressure Altitude Source 2 if installed D D Garmin Altitude Encod...

Page 348: ...000 Display Interfaced Active Traffic System None TCAD TAS TCAS NOTE If the system includes all ofthe following components GTX 345R 0950 1000 Display and TCAD or TAS TCAS Then the aircraft is no longer equipped with a TSO compliant active TCAD TAS or TCAS system Any operational requirement to be equipped with such system is no longer met I 90 00734 15 Rev 2 Page 10 of 18 AFMS Garmin GTX 33X and 3X...

Page 349: ...al Regulations Extended Squitter Global Navigation Satellite System Garmin Navigation System Global Positioning System Garmin Transponder Garmin Touchscreen Navigator International Civil Aviation Organization Line Replaceable Unit Pressure Altitude Broadcast Inhibit Pilot Operating Handbook Satellite Based Augmentation System Software Traffic Collision Avoidance System Traffic Information Service ...

Page 350: ...transponders Table 2 Required Equipment 2 2 ADS B Out The GTX 33X and GTX 3X5 only comply with 14 CFR 91 227 for ADS B Out when all required functions are operational When the system is not operational ADS B Out transmit failure messages will be present on the remote control display interface or the GTX 330 or GTX 3X5 panel display 2 3 TIS Traffic Display with User Navigation Angle Display ofTIS t...

Page 351: ...y GTX 345 Only Do not use datalin k weather information for maneuvering in near or around areas ofhazardous weather Information provided by datalink weather products may not accurately depict current weather conditions Do not use the indicated datalink weather product age to determine the age ofthe weather information shown by the datalink weather product Due to time delays inherent in gathering a...

Page 352: ...SBAS receiver is inoperative or GPS position information is not available or invalid the GTX will no longer be transmitting ADS B Out data For GTX 330 installations NO ADSB annunciator illuminated Interfaced GPS position sources VERIFY VALID POSITION For GTX 3X5 installations NO 1090ES TX annunciator illuminated Interfaced GPS position sources VERIFY VALID POSITION For GTX 33 and GTX 3XSR installa...

Page 353: ...ted by the pilot the GlOOO display will provide nuisance alerts unless power is removed from Transponder 1 Transponder 1 Failed Transponder 2 Active Transponder I Circuit Breaker PULL AFMS Garmin GTX 33X and 3X5 XPDR with ADS B FAA APPROVED 190 00734 15 Rev 2 Page 15 of 18 ...

Page 354: ...ctivating or deactivating emergency status for both transponder and ADS B Out functions Details on performing these procedures are located in the GTX 330 330D Pilot s Guide and GTX 3X5 Series Transponder Pilot s Guide 4 1 Unit Power On For GTX 330 installations GTXMode VERIFY ALT NO ADSB CONSIDERED For GTX 3X5 installations GTX Mode VERIFY ALT NO 1090ES TX CONSIDERED NOTE The NO ADS B or NO I090ES...

Page 355: ... Annunciation or associated display annunciations must be EXTI GUISHED for the system to meet the requirements specified in 14 CFR 91 227 This system must be operational in certain airspaces after January I 2020 as specified by 14 CFR 91 225 Section 5 PERFORMANCE No change Section 6 WEIGHT AND BALANCE See current weight and balance data AFMS Garmin GTX 33X and 3X5 XPDR with ADS 8 FAA APPROVED 190 ...

Page 356: ...NS 480 Pilot s Guide 190 00502 00 Rev D or later GTX 3X5 Series Transponder GI 000 Pilot s 90 01499 01 Rev A or later Guide 7 1 GTX TIS Behavior The TIS Standby Operate controls for GTX 33 330 and GTX 335 units only function when the aircraft is airborne 7 2 GTX 345R and G950 1000 No Bearing Traffic Alerts No visual indication is provided for no bearing traffic alerts Only an aural indication ofth...

Page 357: ... ...

Page 358: ...Circulars 10 12 FAA General Aviation News 10 15 FAA Accident Prevention Program 10 15 Additional Information 10 16 General Information on Specific Topics 10 17 Maintenance 10 17 Hazards of Unapproved Modifications 10 19 Flight Planning 10 20 Passenger Information Cards 10 20 Stowage of Articles 10 21 Flight Operations 10 21 General 10 21 Preflight Inspection 10 21 Weight and Balance 10 22 Autopilo...

Page 359: ...ins 10 36 Descent 10 38 Vortices Wake Turbulence 10 39 Takeoff and Landing Conditions 10 40 Medical Facts for Pilots 10 40 General 10 40 Fatigue 10 41 Hypoxia 10 41 Hyperventilation 10 43 Alcohol 10 43 Drugs 10 45 Scuba Diving 10 45 Carbon Monoxide and Night Vision 10 45 Decompression Sickness 10 46 A Final Word 10 47 10 2 May 1994 ...

Page 360: ...oughly familiar with your airplane Know its limitations and your own Maintain your currency or fly with a qualified instructor until you are current and proficient Practice emer gency procedures at safe altitudes and airspeeds prefer ably with a qualified instructor pilot until the required action can be accomplished without reference to the manual Peri odically review this safety information as p...

Page 361: ...nd the other operating and maintenance manu als which accompany the airplane that FAA requirements for ratings certifications and review be scrupulously com plied with and that you allow only persons who are properly licensed and rated and thoroughly familiar with the contents of the Pilot s Operating Handbook and FAA Approved Air plane Flight Manual to operate the airplane IMPROPER OPERATION OR M...

Page 362: ...uctor until you are current Practice until you are proficient Preplan all aspects of your flight including a proper weather briefing and adequate fuel reserves Use services available weather briefing inflight weather and Flight Service Station Carefully preflight your airplane Use the approved checklist Have more than enough fuel for takeoff plus the trip and an adequate reserve Be sure your weigh...

Page 363: ...on can be accomplished without reference to the manual Keep your airplane in good mechanical condition Stay informed and alert fly in a sensible manner DON TS Don t take off with frost ice or snow on the airplane Don t take off with less than minimum recommended fuel plus adequate reserves and don t run the tank dry before switching Don t fly in a reckless show off or careless manner Don t fly int...

Page 364: ...ation of your airplane When the airplane was manufac tured it was equipped with one or more of the following placards Owner s Manual FAA Approved Airplane Flight Manual FAA Approved Airplane Flight Manual Supple ments Pilot s Operating Handbook and FAA Approved Air plane Flight Manual Beech has revised and reissued many of the early manuals for certain models of airplanes in GAMA Standard Format a...

Page 365: ...ons of BEECHCRAFT Safety Communiques to BEECH CRAFT Owner addresses as listed by the FAA Aircraft Reg istration Branch List and the BEECHCRAFT International Owner Notification Service List While this information is dis tributed by Beech Aircraft Corporation Beech can not make changes in the name or address furnished by the FAA The owner must contact the FAA regarding any changes to name or address...

Page 366: ...st may be made by using the owner notification request card furnished with the loose equipment of each airplane at the time of delivery or by a letter requesting this service referencing the specific airplane serial number owned Write to Supervisor Special Services Dept 52 Beech Aircraft Corporation P O Box 85 Wichita Kansas 67201 0085 From time to time Beech Aircraft Corporation issues BEECHCRAFT...

Page 367: ...ment regulations The regulations are designed for your protection and the protection of your passengers and the public Com pliance is mandatory AIRWORTHINESS DIRECTIVES FAR 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 S INFORMATION MANUAL The Air...

Page 368: ...ing Radio Phraseology and Technique Mountain Flying Airport Operations Wake Turbulence Vortices Clearances and Separations Medical Facts for Pilots Preflight Bird Hazards Departures IFR Good Operating Practices En route IFR Airport Location Directory Arrival IFA All pilots must be thoroughly familiar with and use the infor mation in the AIM ADVISORY INFORMATION NOTAMS Notices to Airmen are documen...

Page 369: ...iation bookstores or at FBO s These documents are subject to periodic revision Be certain the Advisory Circular you are using is the latest revision available Some of the Advisory Circulars of interest to pilots are oo s 00 24 00 30 00 45 00 46 2Q 5 20 32 20 35 20 43 20 105 20 113 20 125 10 12 Aviation Weather Thunderstorms Rules of Thumb for Avoiding or Minimizing Encounters with Clear Air Turbul...

Page 370: ...s Markings and Placards Airplanes Availability of Industry Developed Guide lines for the Conduct of the Biennial Flight Review The Accident Prevention Counselor Pro gram Pilot Transition Courses for Complex Single Engine and Light Twin Engine Air planes Flight Training Handbook Pilot s Handbook of Aeronautical Knowl edge Instrument Flying Handbook Hazards Associated with Spins in Airplanes Prohibi...

Page 371: ...nce Handbook Maintenance and Handling of Air Driven Gyroscopic Instruments Use of Alternate Grades of Aviation Gaso line for Grade 80 87 and Use of Automotive Gasoline Noise Hearing Damage and Fatigue in General Aviation Pilots Unreliable Airspeed Indications Operational and Maintenance Practices for Emergency Locator Transmitters and Receivers Gyroscopic Instruments Good Operating Practices Impor...

Page 372: ...ion specialists to each Flight Standards and General Aviation District Office to organize accident prevention program activities In addition there are over 3 000 volunteer airmen serving as accident prevention counselors sharing their technical expertise and professional knowledge with the general aviation commu nity The FM conducts seminars and workshops and dis tributes invaluable safety informa...

Page 373: ... eral Aviation Accident Prevention Program These can be obtained at FAA Offices Weather Stations Flight Service Stations or Airport Facilities Some of these are titled 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 Guide Thunderstorms...

Page 374: ...ted and promptly corrected Schedule your maintenance regularly and have your air plane serviced by a reputable organization Be suspicious of bargain prices for maintenance repair and inspections It is the responsibility of the owner and the operator to assure that the airplane is maintained in an airworthy condi tion and that proper maintenance records are kept Use only genuine BEECHCRAFT or BEECH...

Page 375: ...ly disclaims any responsibility for malfunctions failures damage or injury caused by use of non BEECHCRAFT parts Airplanes operated for Air Taxi or other than normal opera tion 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 the operat...

Page 376: ...er Supple mental Type Certificates STC s Before installing an STC on your airplane check to make sure that the STC does not conflict with other STC s that have already been installed Because approval of an STC is obtained by the individual STC holder based upon modification of the original type design it is possible for STC s to interfere with each other when both are installed Never install an un...

Page 377: ...e track and stations and make a list for quick reference It is strongly recommended a flight plan be filed with Flight Service Sta tions even though the flight may be VFR Also advise Flight Service Stations of changes or delays of one hour or more and remember to close the flight plan at destination The pilot must be completely familiar with the performance of the airplane and performance data in ...

Page 378: ... utilized to provide space for seat displacement If hard solid objects are stored beneath seats the energy absorbing feature is lost and severe spinal injuries can occurto occupants Prior to flight pilots should insure that articles are not stowed beneath seats that would restrict seat pan energy absorption or penetrate the seat in event of a high vertical velocity accident FLIGHT OPERATIONS GENER...

Page 379: ...g speed will be higher rate of climb the cruising speed and the range of the airplane at any level of fuel will all be lower than shown in the Performance section If an airplane is loaded so that the C G is forward of the for ward limit ii will require additional control movements for maneuvering the airplane with correspondingly higher con trol forces The pilot may have difficulty during takeoff ...

Page 380: ...d in the Airplane Flight Manual Supplements Ensure a full understanding of the methods of engagement and disengagement of the autopi lot and trim systems Compare the descriptions and procedures contained in the Supplements to the actual installation in the airplane to ensure that the supplement accurately describes your instal lation Test that all buttons switches and circuit breakers function as ...

Page 381: ...lot malfunction from an electric trim system malfunction The safest course is to deactivate both Do not re engage either system until after you have safely landed Then have the systems checked by a qualified service facility prior to further flight Depending upon the installation on your airplane the follow ing additional methods may be available to disengage the autopilot or electric trim in the ...

Page 382: ...H FLT switch on the autopilot control ler if installed NOTE After the autopilot is positively disengaged it may be necessary to restore other electrical functions Be sure when the master switches are turned on that the autopilot does not re engage The above ways may or may not be available on your auto pilot It is essential that you read your airplane s AFM SUPPLEMENT for your autopilot system and...

Page 383: ...he air plane Airplanes are designed so that flutter will not occur in the normal operating envelope of the airplane as long as the airplane is properly maintained In the case of any airplane decreasing the damping and stiffness of the structure or increasing the trailing edge weight of control surfaces will tend to cause flutter If a combination of those factors is suf ficient flutter can occur wi...

Page 384: ...e which could create an increased trailing edge heavy control surface and flutter If an excessive vibration particularly in the control column and rudder pedals is encountered in flight this may be the onset of flutter and the procedure to follow is 1 IMMEDIATELLY REDUCE AIRSPEED lower the land ing gear if necessary 2 RESTRAIN THE CONTROLS OF THE AIRPLANE UNTIL THE VIBRATION CEASES 3 FLY AT THE RE...

Page 385: ... Airplane may be momentarily out of control Occupants are thrown violently against the belts and back into the seat Unsecured objects are tossed about Occupants require seat belts and occasion ally are thrown against the belt Unsecured objects move about Occupants may be required to use seat belts but objects in the airplane remain at rest Thunderstorms squall lines and violent turbulence should b...

Page 386: ...cessive airspeed you run the risk of structural damage or failure on the other hand if your air speed is too low you may stall If turbulence is encountered reduce speed to the turbulent air penetration speed if given or to the maneuvering speed which is listed in the Limitations section of the Pilot s Oper ating Handbook and FAA Approved Airplane Flight Manual These speeds give the best assurance ...

Page 387: ... downdrafts The prediction of wind shears is far from an exact science Monitor your airspeed carefully when flying near storms particularly on approach Be mentally prepared to add power and go around at the first indication that a wind shear is being encountered WEATHER RADAR Airborne weather avoida nce radar is as its name implies for avoiding severe weather not for penetrating it Whether to fly ...

Page 388: ...echoes should be separated by at least 40 miles before you fly between them With weaker echoes you can reduce the distance by which you avoid them Above all remember this never regard any thunderstorm lightly Even when radar observers report the echoes are of light intensity avoiding thunderstorms is the best policy The following are some do s and don ts of thunderstorm avoid ance 1 Don t land or ...

Page 389: ... your shoulder harness and secure all loose objects 10 Plan and hold your course to take you through the storm in minimum time 11 To avoid the most critical icing establish a penetration altitude below the freezing level or above the level of 15 C 12 Verify that pitot heat is on and turn on carburetor heat or engine anti ice Icing can be rapid at any altitude and cause almost instantaneous power f...

Page 390: ... should not be taken as assurance that mountain wave turbulence will not be encountered A mountain wave downdraft may exceed the climb capability of your airplane Avoid mountain wave downdrafts VFR LOW CEILINGS 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 ...

Page 391: ...erpretations illusions result and may confuse the pilot s conception of the attitude and position of his air plane Under VFR conditions the visual sense using the horizon as a reference can override the illusions Under low visibil ity conditions night fog clouds haze etc the illusions pre dominate Only through awareness of these illusions and proficiency in instrument flight procedures can an airp...

Page 392: ...uld not be made or it should be discontinued as soon as possible The result of vertigo is loss of control of the airplane If the loss of 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 subje...

Page 393: ...ivated by interruption of circuits circuit breakers or fuses Compliance with this requirement is especially important in all high performance single engine airplanes during simulated engine out practice or stall dem onstrations because the stall speed is critical in all low speed operation of airplanes Training should be accomplished under the supervision of a qualified instructor pilot with caref...

Page 394: ...tentional spins are entered by delib erately inducing a yawing moment with the controls as the airplane is stalled Inadvertent spins result from the same combination stall plus yaw That is why it is important to use coordinated controls and to recover at the first indication of a stall when practicing stalls Always remember that extra alertness and pilot techniques __ are required for slow flight ...

Page 395: ...avoidance is your best protection against an inadvertent spin MAINTAIN YOUR AIRSPEED In airplanes not certificated for aerobatics spins are prohib ited If a spin is entered inadvertently Immediately move the control column full forward and simul taneously apply full rudder opposite to the direction of the spin continue to hold this position until rotation stops and then neutralize all controls and...

Page 396: ...rtices The larger and heavier the airplane the more pronounced and turbulent the wakes will be Wing tip vortices from large heavy airplanes are very severe at close range degenerating with time wind and distance These are rolling in nature from each wing tip In tests vor tex velocities of 133 knots have been recorded Encounter ing the rolling effect of wing tip vortices within two minutes after pa...

Page 397: ...friction Snow and ice covered runways are also hazardous The pilot should also be alert to the possibility of the brakes freezing Use caution when taking off or landing during gusty wind conditions Also be aware of the special wind conditions caused by buildings or other obstructions located near the runway MEDICAL FACTS FOR PILOTS GENERAL When the pilot enters the airplane he becomes an integral ...

Page 398: ...arm 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 sensation sweating reduced visual field sleepiness blue coloring of skin fingernails and lips and beh...

Page 399: ...that require or may require the use of supplemental oxygen should be thoroughly familiar with the operation of the airplane oxygen systems A preflight inspection of the system should be performed including proper fit of the mask The passengers should be briefed on the proper use of their oxygen system before flight Pilots who wear beards should be careful to ensure that their beard is carefully tr...

Page 400: ...usly slow your breathing rate until symptoms clear and then resume nor mal breathing rate Normal breathing can be aided by talk ing aloud ALCOHOL Common sense and scientific evidence dictate that you must not fly as a crew member while under the influence of alcohol Alcohol even in small amounts produces among other things A dulling of critical judgement A decreased sense of responsibility Diminis...

Page 401: ...bout one third of an ounce per hour Even after the body completely destroys a moderate amount of alcohol a pilot can still be severely impaired for many hours by hangover The effects of alcohol on the body are magnified at altitudes as 2 oz of alcohol at 18 000 feet produce the same adverse effects as 6 oz at sea level Federal Aviation Regulations have been amended to reflect the FAA s growing con...

Page 402: ...dous Even simple home or over the counter remedies and drugs such as aspirin anti histamines cold tablets cough mixtures laxatives tranquil izers and appetite suppressors may seriously impair the judgment and coordination needed while flying The safest rule is to take no medicine before or while flying except after consultation with your Aviation Medical Examiner SCUBA DIVING Flying shortly after ...

Page 403: ...nitrogen bubble formation in body tissue as the ambient air pressure is reduced by climbing to higher alti tudes The symptoms are pain in the joints abdominal cramps burning sensations in the skin visual impairment and numbness Some of these symptoms are similar to hyp oxia The only known remedy for decompression sickness is recompression which can only be accomplished in an unpressurized airplane...

Page 404: ...s is even more remarkable Radar RNAV LORAN sophisticated autopilots and other devices which just a few years ago were too large and pro hibitively expensive for general aviation size airplanes are becoming increasingly commonplace in even the smallest airplanes It is thus that this Safety Information is directed to the pilot for it is in the area of the skill and proficiency of you the pilot that ...

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