PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL

lnternational Distrigutors or Dealers can provide recommended modif ication, service, and operating procedures issued by both FAA and Beech Aircraft Corporation, which are designed to get maximum utility and safety from this airPlane. USE OF THE HANDBOOK The Pilot's Operating Handbook is designed so that nec- essary documents may be maintained for the safe and efficient operation of the airplane" The handbook has been prepared in loose leaf form for ease in maintenance and in a convenient size for storage. The handbook has been arranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions: ' Section 1 General Section 2 Limitations Section 3 EmergencY Procedures Section 4 Normal Procedures Section 5 Performance Section 6 Weight and BaianceTEquipment List Section 7 Systems DescriPtion Section 8 Handling, Servicing and Maintenance Section 9 Supplements Section 1O Safety lnformation 1-4 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Section I General NOTE Except as noted, all airspeeds quoted in this handbook are lndieated Airspeeds (lAS) and as- sume zero instrurnent error. Due to the large variety of airplane configurb- tions avaiiable through optional equipment, it should be noted that in describing and illustrating the handbook, optional equipment may not be designated as such in every case. Through variations provided by custom designing, the illustrations in thls handbook will not be typical of every airplane. Neither Service Publications, Reissues, nor Re- visions are automAtically provided to the holder of this handbook. For information on how to obtain "Revision Service" applieable to this handbook, consult any BEECHCRAFT Aero or Aviation Center or lnternational Distributor or Dealer or refer to the latest revision of BEECH- CRAFT Seruiee lnstructions No. 0250-010" BEECH AIRCRAFT CORPORATION EX. PRESSLY RESERVES THE RIGHT TO SUPER. SEDE, CANCEL AND/OR DECLARE OB- SOLETE ANY PART, PART NUMBERS, KITS OR PUBLICATION THAT MAY BE REFERENCED IN THIS HANDBOOK WITHOUT PRIOR NOTICE" \! REVISING THE HANDBOOK lmmediately following the title page is the "Log of Revisions" paCe(s).The Log of Revisions pages are used for maintaining a listing of all effective pages in the hand- -oook (except the SUPPLEMENTS section), and as a record of revisions to these pages. ln the lower right corner of the outlined portion of the Log of Revisions is a box containing October 'l 979 1-5 Section I General BEECHCRAFT Sport lll MusketeerA23-19, 19A a capital letter which denotes the issue or reissue of the handbook. This letter may be suffixed by a number which - indicates the numerical revision. When a revision to any information in the handbook is made, a new Log of Re- visions will be issued. All Logs of Revisions must be re- tained in the handbook to provide a current record of ma- terial status until a reissue is made' WARNING When this handbook is used for airplane operational purpose it is the pilot's respon- sibility to maintain it in current status. SUPPLEMENTS REVISION BECORD Section lX contains supplements and a Log of Supple- ments page" On the "Log" page is a listing of the supple- mental equipment available for installation on the BEECH- CRAFT airplane. Upon receipt of a new or revised supplement, compare the "Log" page just received with the"existing "Log" page in the manual. Retain the "Log" page with the latest date on the bottom of the page (this log will usually have the greater number of entries) and discard the other log. VENDOR.ISSUED STC SUPPLEMENTS When a new airplane is delivered from the factory, the handbook delivered with it contains either an STC. .- (Supplemental Type Certificate) Supplement or a Beech Flight Manual Supplement for every installed item requiring a supplement. lf a new handbook for operation of the airplane is obtained at a later date. it is the responsi- bility of the owner/operator to ensure that all required STC Supplements (as well as weight and balance and other pertinent data) are transferred into the new handbook- 1-6 october 1979 BEECHCRAFTSpon ll! lVlusketaerA23-1 9, 1 9A _l_ 14.5" 6'2" DIAMETER ,4, o" 32'9" 1o'8', Section I General 1',10" I October 'l 979 AIRPLANE THREE-VIEW 1-7 Section I General BEECHCRAFT SPort ltl MusketeerA23-19, 19A GROUND TURNING CLEARANCE @ Radius for Wing Tip @ Radius for Nose Wheel @ Radius for lnside Gear @ Radius for Outside Gear 23 ft. 11 in. 9 ,t. 10 in. \- 2 ft. 0 in. 13 ft. 0 in. TURNING RADII ARE CALCULATED USING FULL STEER- ING. ONE BRAKE AND PARTIAL POWER. 1-8 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Section I General DESCRIPTIVE DATA \ rructrur Airplane is e-q.uipped with an Avco Lycoming O-320-E2B, ,.6-32O-EZC or O-320-E3D engine rated at 150 "horsepowei. '-' Take-off and maximum continuous operation (sea level): 27OO rpm, full throttle. Engine cooling has been demonstrated for a 10Oo F day" PROPELLER Sensenich M74DM-O-58 or 74DM6-O-58 fixed-pitch, rwo-blade propeller. Static rpm at maximum permissible throttle settings: Not over 24OO rpm and not under 2300 rpm. No additional tolerance permitted" Diameter 74 inehes, no cutoff permitted^ FUEL Aviation Gasoline 80/87 (red) minimum grade or lOOLL iblue) or 'l OO (green). *59.8-gallon system (29.9 gallons each tank) T58"8 gallons usable Each tank has provisions for partial filling to: 20 gallons eaeh tank .. 38.8 gallons usable 15 gallons each tank . . 28.8 gallons usable October 1979 1-g a Section I General BEECHCRAFT Sport lll MusketeerA23-19, 19A 2205 lbs 220O lbs 22O0 lbs Maximum Ramp Weight .. Maximum Take-Off Weight Maximum Landing Weight Maximum Ramp Weight .. Maximum Take-Off Weight Maximum Landing Weight After compliance with BEECHCRAFT S.l. No. 0624-281: *59.8-gallon system (29.9 gallons each tank) . . . " " "52.2 gallons usable Each tank has.provisions for partial f illing to: 20 gallons each tank . . 32.2 gallons usable 15 gallons each tank . " 22.2 gallons usable '-.' *Value given is nominal. Tank capacity will vary with temperature and manufacturing tolerances. OIL CAPACITY The eil capacity is 8 quarts APPROVED 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. SEBVICING AND MAINTENANCE section for a list of approved products. MAXIMUM CERTIFICATED WEIGHTS NORMAL CATEGORY (423-t 9) NORMAL CATEGORY (19A) (423'19 when kit 23-5003 is installed) 2255 lbs 2250 lbs 2250 lbs 1-10 October 1979 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A uflLtTY CATEGORY (A23-t 9) uTtLtTY I ACROBATTC CATEGORY (t 9A) Maximum Ramp Weight . " Maximum Take-Off Weight Maximum Landing Weight ALL CANFIGURATIONS Maximum Zero Fuel Weight lVlaximum Weight in Baggage Compartment ., o CABIN AND ENTRY DIMENSIONS Length (maxirnum) Height (maximum) Width (maximum) Cabin Door Section I General 2035 lbs 203O lbs 2030 lbs No Structural Limit ". " 34O lbs. 7 ft 11 in" .4ftOin. " 3ft5in. 36 in. wide by 38 in. high 28.5 cu ft 15.O7 lbs/sq ft . 14.67 lbsuhp 15.41 lbs/sq ft . 15.00 lbsZhp BAGGAGE SPACE Cornpartment Volume SPECIFIC LOADINGS (2200 lbs.) Wing Loading Power Loading SPECIFIC LOADINGS (2250 lbs.) Wing Loading Power Loading October 1 979 1-1 1 Section I General BEECHCRAFT Sport lll MusketeerA23-19, 19A SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following Abbreviations and Terminologies have been listed for convenience and ready interpretation where used within this handbook. Whenever possible, they have been categorized for ready reference. GENERAL AIRSPEED TERMINOLOGY CAS Catibrated Airspeed is the indicated speed of an airplane. corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. GS Ground Speed is the speed of an airplane relative to the ground. lndicated Airspeed is the speed of an airplane as shown on the airspeed indicator. IAS values published in this handbook assume zero instrument error. KCAS Calibrated Airspeed expressed in "knots" KIAS lndicated Airspeed expressed in "knots". TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature, and compressibility. IAS 1-12 October 1979 BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A V4 Vrr Vrug Maneuvering Speed is the maximum speed at which application of full available aero- dynamic control will not overstress the airBlane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a pre- scribed extended position Never Exceed Speed is the speed limit that rnay not be exceeded at any time. Maximum Structural Cruising Speed is the speed that shduld not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the mininrum steady flight speed at which the airplane is controllable rn the landing configuration Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance Best Rate-sf-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible tim9. . Reeommended Climb Speed for enroute climb Section I General Vg Vruo or Vg Vso Vy Cruise Climb October 'l 979 1-13 Section I General BEECHCRAFT Sport lll MusketeerA23-19, 19A METEO ROLOGI CAL TERMINOLOGY ISA lnternational Standard Atmosphere in which (1) The air is a dry Perfect gas; (2) "The temperature at sea level is 'l 5o Celsius (59o Fahrenheit); (3) The pressure at sea tevel is 29'92 in Hg. (1013.2 millibars); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.50 C (-69.70 F) is -0.00198o C (-O.0O35660 F) Per foot and zero above that altitude" OAT Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indica- tions adjusted for instrument error and comPressibility effects, or ground meteorological 9UrCeS. lndicated The number act;lly read from an Pressure altimeter when the barometric sub- Altitude scale has been set to 29.92 in Hg. (1013.2 millibars)' Pressure Altitude measured from standard Altitude sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. ln this Handbook, altimeter instrument errors are assumed to be zero. Position errors maY be obtained from the Altimeter / Correction GraPh. I..: 1-14 October 1979 BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Station Pressure Throttle eontrol Mixture Control Actual atmospheric pressure at field elevation. The wind velocities reeorded as variables on the charts of this hand- book are to be understood as the head- wind or tailwind comPonents of the reported winds. Used to eontrol power by intro- ducing fuel-air mixture into the intake passages of the engine. This control is used to set fuel flow in all modes of oPeration and euts off fuel completelY for engine shut down. This indicator is used to identify the lean and best ppwer fuel flow for various power settings. lndicates the rpm of the engine/ propeller. Seetion I General Wind POWER TERMINOLOGY Take off and Highest power rating Maximum not lirfiited by time" Continuous ENGINE CONTROLS AND INSTRUMENTS '\- EGT (Exhaust Gas Temperature lndicator) \.-- Tachometer October 1979 1-15 Section I General AIRPLANE PERFORMANCE AND FLIGHT PLANNING TEBMINOLOGY Climb Gradient BEECHCRAFT Sport lll MusketeerA23-19, 19A Demonstrated Crosswind Velocity MEA Station Route Segment GPH PPH Pounds per hour WEIGHT AND BALANCE TERMINOLOGY Reference An imaginary vertical plane from Datum which all horizontal distances are measured for balance purposes. The ratio of the change in.height during a portion of a climb, to the horizontal distance traversed in the same time interval. The demonstrated crosswind velociry is the velocity of the crosswind com- ponent for which adequate control of the airplane during take-off and land- ing was actually demonstrated during certification tests. Minimum enroute IFR altitude A part of a route. Each end of that part is identified by: (1) a geograph- ical location; or (21 a point at which a definite radio fix can be established U.S. Gallons per tiour A location along the airplane fuselage usually given in terms of distance from the reference datum. 1-16 October 'l 979 BEECHCRAFT Sport lll lVlusketeer A23- 1 9, 1 9A Arm Moment Airplane Center of Gravity (c.G.) C"G. Arm C.G. Limits Unusable Fuel Standard Empty Weight Basic Empty Weight The horizontal distance from the ref- erence 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 bal- ance calculations by reducing the number of digits.) The point at which an airplane would balance if suspended. lts distance from the reference datum is found by dividing the total moment by the total f,veight of the airplane. The arm obtained by adding the air- plane's individual moments and dividing the sum by the total weight. The extreme center of gravity loca- tions within which the airplane must be operated at a given weight. Fuel remaining after a runout test has been completed in accordance with governmental regulations. Weight of a standard airplane including unusable Juel, full operbting fluids and full oil" Standard empty weight plus optional equipment. Section I General Usable Fuel Fuel available for flight planning October 'l 979 "t-17 Section I General Payload Useful Load Maximum Ramp Weight Maximum Take-off Weight Maximum Landing Weight Zero Fuel Weight Tare Leveling Psints Jack Points BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Weight of occupants, cargo and baggage. Difference between take-off weight, or. ramp weight if applicable, and basic empty weight. Maximum weight approved for ground maneuvering. (lt includes weight of start, taxi, and run-up fuel). Maximum weight approved for the start of the take-off run. Maximum weight approved for the landing touchdown. Weight exclusive of usable fuel. The weight of chodks, blocks, stands, etc. used on the scales when weighing an airplane. Those points which are used during the weighing process to level the airplane. Points on the airplane identified by the manufacturer as suitable for supporting the airplane for weighing or other purposes. 1-18 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A SECTION II LIMITATIONS TABLE OF EONTENTS SUBJECT Airspeed Limitations Airspeed lndicator Markings Power Plant LimitationS Engine Operating Limitations ...... Fuel Grades Fuel Additives."". Oil Specifications . Prspeller Specifications ...'...' Power Plant lnstrument Markings . . IVliscellaneous lnstrument Markings Weight Limits . Center of Gravity Limits " Reference Datum Maneuver Limits' Flight Load Factors Minimum Flight Crew Kinds of Operation Limits . Equipment Required for Various Conditions of Flight ... "..... ". " : Fuel .. Total Fuel Fuel Management . Placards Octob€r 1979 2-", PAGE . 2-3 . 2-4 2-4 2-5 2-5 2-5 2-5 2-5 2-6 2-7 2-7 2-8 2_8 ,_q 2-9 . . 2-19 . " 2-19 2-20 - 2-29 2-6 2-10 Section ll Limitations INTENTIONALLY LEFT BIANK BEECHCRAFT Sport lll MusketeerA23-19, 19A 2-2 October 1979 The limitations included in this section have been approved by the Federal Aviation Administration. The following limitations must operation of this airplane. be observed in the \- AIRSPEED LIMITATIONS BEECHCRAFTSpoTt lll MusketeerA23-19, 19A Seetion ll Limitations SPEED cAs tAs REMARKS KNOTS MPH KNOTS MPH Never Exceed \foE 152 175 152 175 Do not exceed this speed in any operation Maximum Structural eru ising VNO or VC 133 153 134 154 Do not exceed this speed except in smooth air and then only with caution Maneuvering VA 116 133 115 132 Do not make full or abrupt control movements above this speed Maximum Flap Extensiony' Extended vre 96 110 97 111 Do not extend flaps or operate with flaps ex- tended above this speed October 1979 2-3 Section ll Limitations BEECHCBAFTSPoTT lll MusketeerA23-19, 19A *AIRSPEED INDICATOR MARKINGS " The limits of the arcs on the airspeed indicator are marked in CAS values. POWER PLANT LIMITATIONS ENGINE One Avco Lycoming engine model O-320-E28, O-32O-E2C or O-320-E3D engine rated at 150 hp. Take-off and Maximum Continuous Power . . Full Throttle or 27OO rPm whichever occurs first MARK- ING CAS lAS SIGNIF. ICANCE KTS MPH KTS MPH White Arc 50-96 57-1 10 48-97 55-1 1 1 Full Flap Operating Range Green Arc 60-1 33 69- 1 53 58-1 34 67-154 Normal Operating Range Yellow Arc 1 33-1 52 153-175 134-152 154-175 Operate With Caution, Only in Smooth Air Red Line 152 175 152 175 Maximum Speed For All Operations 2-4 October 1979 BEECHCRAFT Sport lll lVlusketeerA23- 1 9, 1 9A Section ll Limitations OPERATING LIMITATIANS \ Engine Speed 27OO rpm "Oil Temperature .. 245oF Oil Pressure Minimum .... . 25 psi Maximum 1OO psi \ : Fuel Pressure Minimum ... " O.5 psi Maximum ... " 6.0 psi Mixture - Set per leaning instructions on performance eharts. \ "All temperatures are established for a 1O0oF day. FUEL GRADES Aviation Gasoline 80/87 (red) minimum grade or lOOLL (blue) or 'lO0 (green). FUEL ADDITIVES Alcor TCP Concentrate mixed according to the instruc- tions provided by Alcor. lnc. OIL SPECIFICATIONS Avco Lycoming Specification Nurnber 3O1E approves for use lubricating oils which conform to both MIL-L-60828 straight mineral type and MIL-L-22851 ashlessdispersant lubricants for airplane engines. Refer to the Approved Engine Oils table in the HANDLING. SERVICING AND MAINTENANCE section for a list of approved products. PROPELLER SPECIFI CATIONS Sensenich M74DM-O-58 or 74DM6-O-58 fixed-piteh, two-blade propeller. Static rpm at maximum permissible \ throttle settings: Not over 2400 rpm and not under 23OO rpm. No additional tolerance permitted. Diameter 74 inches, no cutoff permitted. October 1979 2-5 Section ll Limitations POWER PLANT INSTRUMENT MARKINGS OIL TEMPEBATURE Caution (Yellow Arc) Operating Range' (Green Arc) Maximum (Red Line) OIL PRESSURE Minimum Pressure (Yellow Arc) Operating Range (Green Arc) . . Maximum Pressure (Red Line) . FUEL PRESSURE Operating Range (Green Arc) TACHOMETER Engine Warm-up Normal Operating Range (Green Arc) .. Maximum RPM (Red Radial) BEECHCRAFTSpoTt lll MusketeerA23-19, 19A 600 to 1 200F 1 200 to 2450F ' 2454F 25 to 60 to 6O psi 90 psi \.'lOO psi 0.5 to 6.O psi 8OO to 12OO rpm 22OO to 270O rpm 27O0 rpm MTSCELLAN EOUS INSTRU MENT MARKINGS INSTRUMENT AIR Operating Range (Green Arc) 4.3 to 5.9 in. Hg FUEL OUANTITY After compliance with BEECHCRAFT S.l. No. 0624-281 Yellow Band ... E to 3/8 full 2-6 October 1979 BEEe HCRAFT Sport Ill Musketeer A23- 19, 1 9A Seetion ll Limitations 09€ FutL LtAp g /3 "3 *WEIGHT LIMITS NORMAT CATEGORY (A23-1 9) Maxiinum Ramp Weight ... .. Maximum Tak'e-off '- and tanding Weight 22OO lbs ral Limitation Zero Fuel We Maximu age Compartment 340 lbs NORMAL CATEGORY (19A)(A23-19 when BEECHCBAFT 2255 lbs 2250 lbs Zero Fuel Weight ....". No Struetural Limitation Maximum Baggage Compartment Load 340 lbs uTrLrTY CATEGORY (423-1 9) UTILITY/ACROBATIC CATEGO RY (1 9A) Maximum Ramp Weight .. ... 2035 lbs Maximurn Take-off and Landing weight .. 2030 lbs Zero Fuel Weight ...... No Structural Lirnitation Maximum Baggage Compartment Load (Utility Category Only| . 34O lbs CENTER OF GRAVTTY LIMITS NORMAT CATEGORY (A23-1 9) Forward: 1O7"8 inches aft of datum to 18OO lbs with straight line variation to 112.0 inches al 22OO Ibs. Kit 23-5OO3 is installed) EUfPTy tvl' l,{!6.{lVlaximum'Ramp Weigltt ..... ".. tVlaximum Take-off and Landing Weight October 1979 2-7 Section ll Limitations BEECHCRAFT Sport lll MusketeerA23-19, 19A Aft: 118.3 inches aft of datum at all weights NORMAL CATEGORY (19A) (A23-19 when BEECHCBAFT Kit 23-5003 is installed) Forward: 107.8 inches aft of datum to 18OO lbs with straight line variation to 112"5 at 2250 lbs. Aft: 1'l 8.3 inches aft of datum at all weights UTILITY/ACRO BATIC CATEGO RY Forward: 107.8 inches aft of datum to 18OO lbs with straight line variation to 11O.2 inches aft of datum at 2030 lbs. Aft: 114.0 inches aft of datum at all weights, REFEREf!CE DATUM Datum is 103 inches forward of wing leading edge MAC length is 52.7 inches. ' o MANEUVER LIMITS The A23-19 and 19A airplane is approved for 4 place in the Normal Category and for 2 place in the Utility Category. The 19A is also approved for 2 place in the Acrobatic Category. Maximum slip duration is 3O seconds. NORMAL CATEGORY (2250 POUNDS & 2200 POUNDS) No acrobatic maneuvers approved. uTrLlw CATEGORY (2030 POUNDS) No acrobatic maneuvers are approved except those Iisted below. 2-8 October 1979 \ ACROBAT|C CATEGORY (19A) (2030 POUNDS) For additional approved acrobatic maneuvers see Filot's Operating Handbook and FAA Approved Airplane Flight Manual Supplernent. FLIGHT LOAD FACTORS NORMAL CATEGORY (2250 pOt'NDS & 2200 POUNDS) BEECHCRAFT Sport lll Musketeer A23- 19, 1 9A MANEUVER Chandelle Steep Turn ...... " Lazy Eight Stall (Except Whip) Section ll Limitations ENTRY SPEED (CAS) 116 kts/l33 mph 1 16 kts/133 mph 116 kts/133 mph Use slow deceleration Flight maneuvering load factors Flaps Up Flaps Down UTILITY CATEGORY (2O3O POUNDS) Flight maneuvering load factors Flaps Up Flaps Down ACROBATIC CATEGORY (19A) (2030 POUNDS) Flight maneuvering load factors Flaps Up Flaps Down MINIMUM FLIGHT CREW One (1) Pilot October 1979 2-9 Section ll Limitations BEECHCRAFf SpoTt lll MusketeerA23-19, 19A KINDS OF OPERATION LIMITS 1. VFR day and night 2. IFR day and night REOUIRED EOUIPMENT 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) specifv the minimum numbers and types of airplane instruments and equipment which rnust be installed and operable for various kinds of flight conditions. This includes VFR day, VFR night, IFR day, and IFR night. Regulations also require that all airplanes be certificated by the manufacturer for operations under various flight conditions. At certification, all required equipment must be in operating condition and should be maintained to assure continued airworthiness. lf deviations from the installed equipment were not permitted, or if the operating rules did not provide for various flight conditions. the airplane could - not be flown unless all equipment was operable. With appropriate limitations, the operation of every system or component installed in the airplane is not necessary. when the remaining operative instruments and equipment provide {or continued safe operation. Operation in .- accordance with limitations established to maintain airworthiness, can permit continued or uninterrupted operation of the airplane temporarily" For the sake of brevity, the Required Equipment Listing does not include obviously required items such as wings, rudders, flaps, engine, landing gear, etc. Also the list does not include items which do not affect the airworthiness of 2-10 October 1979 BEECHCRAFT Sport lll Musketeer A23- 19, 1 9A Seetion ll Limitations the airplane such as entertainment systems, passenger convenience items, etc. However, it is important to note that ALL ITEMS WHICH ARE RELATED TO THE AIR- WORTHINESS OF THE AIRPLANE AND NOT INCLUDED ON T}IE LIST ARE AUTOMATICALLY REOUIRED TO BE OPERATIVE. To enable the pilot to rapidly determine the FAA equipment requirements necessary for a f light into specif ic conditions. the following equipment requirements and exeepfions are presented. lt is the f inal resBonsibility of the pilot to determine whether the lack of, or inoperative status of a piece of equipment on his airplane, will limit the eonditions under which he may operate the airplane" FLIGHT IN PROHIBITED WARNING KNOWN ICING CONDITIONS LEGEND Numbers refer to quantities required to be operative for a specified condition. (-) lndicates that the item may be inoperative for the specified condition. (*) Refer to the REMARKS AND/OR EXCEPTIONS column for explicit information or referen.e" October 1979 2-11 BEECHCRAFT SPort lll MusketeerA23-19, 19A Sectisn ll Limitations t4 o a,) () t! a ct) a? o) E LL o L (o a? o) E LL L 0) o- o (E t.9Oo 6 <-r (I!o cc UT B oo- o CE otu ul E E o tho Zo 95 F'= (J 'E z=1C EE =3 O lL o= E .9 E J rui2L E9ao \G a tr _5, =tl{ o a q s z =ur r! 62 6E8 d"Eo October 1979 2-12 Section ll Limitations BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A 6C .9 o ro€cD .Y, .E o.g CiE <-or!O L(J o(o (L XN b; u'l b go I:Eos{ (L OLL O(a0) o-<o- b -c z2o6, tr.EoIlllo L bgCE O- o) HEtLo o- ^o <Eoi: -g(,)o U)P (l)(o -O =o (o- _c >- .no 3! 3,; E 5 9.!O-C E E (,(,14) o z -o 2zurF 2ao-2 =!c O=LLl tL 2-13 Oetober 1 979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Section ll Limitations =? o) b; 3 3x =o;U *'= >{-- Po' s v O= On o-!s .Y c) :E:E BH € d 5* aa 6.1 >.t B or E i s it i;33 E E ; 3" -I c-)-c.=c>; '-oEo6'-oE 0) o) -E L (D'- 6-\ "-EEE BSet 69J(Ed >E.s3E>EI q o t4 {< G q) q \G a t\ Or =t s :o a q s '- o 3 =(E a ?:o) ZO ua!^ .=(E cE .9 .9 (,)o oo o.- ii 9. o (o o oEJC o: F;: Ztr o.:OE Fo56 O= -o J6 lL tn F z5u, LlJ01 irE-8 'rtE o October 1979 2-14 Section ll Limitations BEECHCRAFTSpon ll! MusketeerA23-19, 19A c(o -o-- RO .:E# gEEE O"P O (t , S!* ">9c6; e !iO r (o9(D- k oEo:= oo-*-o cEiio9 '-o-oY 6tP-L !d=(,Y >+ O ^.= EotSq: Lr G (/,-E or6-o*cP E or X O > o-o; o(u oo oo FFBI -Fc\l e:N -rN .9 co a >-o o) (J(JP C:(o 6tJO P;-00)l. c 6'= LU TL z EAL 6ir zYr <F UE o (o .q .: th o 0) a) LL E f,o ,\.= o.f, !? C$ L O-q){: >'-= OLL o-o o o-.= -oEcr or'66fcJ LL I,.TJ LL zul =o- 5 dtr' J lIJ l u- October 1979 2-15 BEECHCRAFT Sport lll Musketeer A23-19, 1 9A Section ll Limitations (o c? o) r6 {c lr.9 86" o) .; 0) o. o 6) -o ID E o E o, : q o a.q) o xt{ ! G * * FCo * r(Y) o a t\ \(B a q s o) E f - @= cP FO- E E'3 g6 ^ol- '= (, c-! o .,2*E € E E EgE68 (J JCtr(L oF -L 0 J z5uJ il ts2 L{a irEx-(E< o6 o October 1979 2-16 eF+ * Fe I F I r + Section ll l-imitations BEECHe RAFT Sport lll MusketeerA23-19,19A tr- q O) oq o *eoc! a? o)o) cr cc TL TL o0) o- o- o tr*O(I]6) iDe q) >C(o (,OO) -tr- rP:f <s9<s (oL(o =f :) o c X B, E ;(Eoh^o",UU :Y-!+;Pi :l Y9Fi;(o> d o I X-Y c or L d .! a? EEa { c ho " 9 -. 6 c E.9 ;3PEt8€ EE E R'E E!. HX 3 e - g k 6..; - y E 6 : <<5><Ei5(JE2 (r, 6EFS <=oa 'ay 2-17 October 1979 Fr ! FF+ * Section ll Limitations BEECHCRAFTSPoTT lll Musketeer A23- 1 9, 1 9A a a t s F z E uj r.rJ d Z 6E-8 ir"3o o 5.e b: o.= Ee '-f, 0)= d9 6= oE o-E == oo o F -tZ E=zG z2 (E., Er L0) oo- 0)tr tro) o Eo o\e a DL i:o oroto -J(J o)-c !l c x.: LU LU (, z tr 3p azz tt) -= zi YA f,'= October 1979 2-18 .p =s t4 o a.q) o x u o ! G t4 to a) q c o \G a s h t s BEECHCRAFTSpoTt lll MusketcerA23- 19, 1 9A Section ll Limitations FUEL IOTAL FUEL with left and right wing fuel systems full; Two *29.9-gallon tanks in wings with a total of *58.8 gallons usable. After compliance with BEECHCRAFT S"l" No. 0624-281 Two *29.9-gallon tanks in wings with a total of "52"2 gallons usable. *Value given is nominal" Tank capacity will vary with temperature and manufacturing tolerances. FUEL MAf{AGEMENT Do not takc off wheri the Fuel Ouantity Gages indieate in the *Yellow Band or with less than 1 1 gallons in each nrain tank. Maximum slip duration: 3O seconds 'Yellow band was installed by BEECHCRAFT S"l. No.0624- 281. Octob€r 1979 2-19 PLACARDS On Lelt Cabin Door or Left Side Panel (CAS) (MB-I thru '- MB-252) Section ll Limitations BEECHCRAFT Sport lll MusketeerA23-19, 19A THIS AIRPTAN€ MUST AE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACAROS, MARKINGS ANO MANUALS NORMAL CATEGORY MAXIMUM DESIGN W€IGHI iTTTN IO WEIGHI AID AAL^NC€ OATA 'OE LOADING INSIAUCIIONS NO ACROEATIC MANEUVERS INCLUOING SPINS APPROVED UTILITY CATEGORY MIXIMUM OESICN WT16HT F''fE IO WfiGHI ANO BALANCE DAIA FOR LOAOTNG rrStFUCrlOrs FLiGNI MANTUVERING !OAO 'ACIOE NO ACROAATIC MANEUVERS APPROVEO EXCEPT THOSE LISTED BELOW: 2o3o tas MAXIMUM CNTRY SPIEO SLOW OECELERAIION slatLs rEtc€PT wHlP STAttSj .!rca1 MANruvrFrNG LOAO .ACtOF MA!IMUM MANTUVTNINC SPE€O 22@ L8S 132 MPH THIS ATRPLANE MUST AE OPERATEO IN COMPUANCE WITH THE OPERATING LIMITATIONS STAIEO IN THE FORM OF PLACARDS- MARKINGS AND MANUALS, NORMAL CATEGORY, MA!IMUM OCSIGi WEIGHY R€fTA TO WEIGHI ANO BAIAICE OAIA roF LoaorNG rftsrRucrroNs fLrGir MArruvtirNG roao racroR NO ACROBATIC MANEUVERS INCLUDIilG SPINS APPROVEO MATIMUM OTSIGN WTIGHI iET€F IO WCI6HI AND BALANCE OATA .OF LOADING INSIiUC'IONS NO ACROAATIC MANEUVERS APPROVEO EXCEPT THOSE LISTEO BETOW: MANEUVER MAXIMUM €NTRY SPE€O csANOalLES r33 MPH LAzY €tcHrs l!3 MPH sr€EP ruRts !!3 td SIAL6 IIICIPI WHIP STALTS} SIOW OECELEFAIION NOT€ MAXIMUM ALIIIUO€ LOSS DUFINo STALT 3OO TI UTIUTY CATEGORY 20r Las 'LI6HT MAfoTUVCRING lOAO 'AC'ON 22@ B3 'IAPS UP € ' -2 2 On Left eabin Door or Left Side Panel (CAS) (MB'253 thru M8-288) 2-20 October 1979 BEECHCRAFTSpoTt lll MusketeerA23-19,19A Seetion ll Limitations On Left Cabin Door or Left Side Panel (CAS) (MB-289 thru \* MB-460) (Airplanes prior to M8-289 when BEECHCRAFT Kit 23-5003 is installed) Cn Left Cabin Door or Left Side PanellMB-l thru MB-252 after compliance with BEECHCRAFT Service Bulletin 67- 23 Revision I ) @ NOTE o MAXIMUM ALTITUDE LOSS DURING.STALL 3OO FT Ocrobor 1979 THIS AIRPLANE MUST BE OP€RATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATEO IN THE FORM OF PUCAROS, MARKINGS AruO MANUALS NORMAL CATEGORY MAXIM!M OESIGN WEI6HT R'TEE IO WEIGHI ANO SALA{C' OATA roc roaorNG rNsTiucTroNs TLI6HT MANFU!fRING LOAO 'ACTOB tr!AXIMUM ilAN6UVTRING S'EIO NO ACROBATIC MANEUVERS INCLUDING SPINS APPAOVEO UTILITY CATEGOFY MAXTMUM OTSTGN WarGHr m$ fls AE'IN TO WE'GXT ANO BALAhCE OAIN 'OR LOAOING INSIGUCIIONS rrlcHr M^fltuvtPrrc LoAo iAcroF rra9s uP * 4 -2 ? NO ACROBATIC MANEUVERS APPBOVED EXCEPT THOSE LISTED BELOW: MAXIMUM ENlAY SPTEO sraL6 r€rcaPl wHrp sIALls 22& US SIOW OECELTRA?ION 2-21 ilOIT MAXIMUM AITIIUDT LOSS OUEIN6 SIAI,L Section ll Limitations BEECHCRAFT Sport lll MusketeerA23-19, 19A PLACARDS (Cont'd) On Left Cabin Door or Left Side Panel (CAS) (Model 19A, MB-322 thru M8-454, ACROBATIC) + + IHIS AIRPTANE.M{.,ST 8E OPERATED IN COMPTIANCE WIIH THE OPERATING I,IMITATIONS STAIEO IN THE FORM OF PIACARDS, MARKINGS AND MANUALS. NORMAT CATEGORY MAIIMUM OTSIGN WIIOH1 IETET TO WIIGXT ANO 'ATANC: OAIA 6r toaolNc INSIIUCTIONS flroHr MANtuv:llNG toao alcld 2250 LBS tlaxur +3!-r9 1 32 MPH MAXIIUM HANIUVTTING 9PTTO NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVEO UIIIITY lt ACROBATIC CATEGORY MAXIilUM O:5IGN WflGBr 2030 tlt lfftr 10 w:loxr aNo laLANct oala rct loaolNG lNsllucTloN5 ft,Gxr MAxtuvtllNc toao facrq tllPt u? +do -30 oowN +2o NO ACROBATIC A4ANEUVERS APPROVEO EXCEPT THOSE LISIED BETOW: TANTUVII MAXIMUM INIIY SITTD cHANO€tlt5 133 M?X tazY ltcHts 133 MPH irEt? luris 133 APH 3IAttS rircEn wrf ll^ttsl Stow otctt[ralDN NOtt: sdltuM Ai[UOa 1O5l OUIING SIAtt ,OO f, sNJ tKX ffilArlONAt tlilll^tloNs sat nacalo ot JUN vlstr IECOMMENOTO ENITY SPTTO I3O MPH I3O MPH I loo MPx 90 MPH I50 MPH I'O MPH BARRET iOLL AttEloN nott sNAP lOlL SPuI S IMMEIMANN tooP + On Right and Left Cabin Doors: (Model l9A, MB-45O thru M8-454, ACROBATIC) o REMOVE DOOR HOLD.OPEN ROD PRIOR TO OPERATION IN ACROBATIC CATEGORY o 2-22 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A On Right Side of lnstrument Panel: (Model l9A" MB-322 thru MB-454, ACROBATIC) An Left Cabin Door: (Model 19A, MB-322 thru MB'454, ACRAEATIC) On Right Cabin Door: (Model l9A, MB-322 thru MB'454, ACROBATIC) t EMERGENCY EXIT TURN HANDLE COUNTER. GLOCKWISE & KICK.OUT TO JETTISON DOOR Section ll Limitations @ CONTINUOUS INVERTED FLIGHT WILL CAUSE LOSS OF OILAND OIL PRESSURE. REAR CG LIMITED ANO GARRYING OF BAGGAGE OR BEAR SEAT PASSENGERS ANO USE OF FLAPS PROHIBITED DURING ACROBATIC MANEUVERS. CAUTION EMERGENCY EXIT TURN HANDLE CLOCKWISE & KICK.OUT TO JETTISON DOOR o @ o o October 1979 ----*r 6i 2-23 Section ll Limitations PLACARDS (Cont'd) BEECHCRAFT Sport lll Musketeer A23-19, 1 9A .E i q) Q G a. o o qJ (u \t to \t a N N(r) a E {Q o) l\ -Q so SE Sq L: a' (uX ox (aY 9xxa soa- o ge Or e3 :\dq 's 9c SH (a() qr 6U sE:-: + 2 iE g;EF = - 'o iEFa ; E .a - cY t: ;i+: E ; t= I! :!si f E .E :9 ;f;iii i; E=? ;; e,?e- E E i 6o ;i*xEE; E rr! BEI:E?:: EiE +;E!;€; : ,-,iE-: ? : - 6 z- '6o -X-: q > : 5E o;=.: o e '-. ;i!E - ; " ;^ aJ. = : o t g: EE .:es: a E : "3o .i* !EE; . . : :;Z'e --.rg- E E E -; o e: 9!:E E { e #d F :E PP:3 = ,g E 8: EIE;:;: g 3;i9 = *: Eisi; ; i g e; r =9 l!3-c= ; a g =5 A:EEAEEEg: EE: =:;i:€E:E: iia Y :E €=E5; ; ; ; i', E ;: ET:iE i' ; !" := cc eF .:6;: ; o I =;rrr i; ;"!:: 5 .E z =< 3;eriE?:c E;E3 !: :;Ett i5 ! i E= ig i!;i: ;E ; E" ;: :i iri;= 5i is; =E ii i;;r! il i! ! *; :": t€EEE =E :E : :E -?a tF! CC .9u e sI 3 a =t o o. Az r o Eu cr October 1 979 2-24 BEECHCRAFT Sport ll! Musketeer A23- 19, 1 9A Seetion ll Limitations On Fuel Selector Panel: (MB-l thru M8-288) On Fuel Selector Panel: (after compliance with BEECHCRAFT S.l. No. 0838) L TANK 29 GAL R TANK 29 GAL OFF OFF L TANK 29 GAL R TANK 29 GAL \2 + + October 1979 2-25 Section tl Limitations BEECHCRAFT Sport lll MusketeerA23-19, 19A PLACARDS (Cont'd) On Fuel Selector Panel: (after compliance with \ BEECHCRAFT S.l. No. 0624-281 and S.l. No. 0838) L TANK. 26 GAL R TANK --- 26 GAL OFF OFF Adjacent to Engine lnstrument Cluster: (after compliance with BEECHCRAFT S.l. No. 0624-281) oo Nol iA(t orr wHtN rutt oulNlrlr GAUGt rNol(Alt5 lN Ytltow or wrIH rt55 lxAN lr G^rroNg rt aA(x rarN taN( aaxrauff 5uP ouialloN ll 3o tt<oNo5 On Upper Right lnstrument Panel: RAISE FLAPS ro INCREASE BRAKE EFFECTIVENESS On Flap Extension Handle ICAS): FLAPS PULL TO EXTEND, MAX SPEED 11O MPH RETRACTED .... FIRST NOTCH .. SECOND NOTCH THIRD NOTCH oo 'l 50 25" 350 2-26 October 1979 BEECHCRAFTSpoTt !ll MusketeerA23-19, X 9A Section ll Limitations On Left Side Panel: TO LEVEL AIRCRAFT * LEVEL BAGGAGE COMPARTMENT FLOOR On Aft Cabin Bulkhead: BAGGAGE COMPARTMENT 34O POUNDS MAXIMUM CAPACITY I Cn Aft Cabin Bulkhead: (Optional with family seat installed) HAT SHELF NO HEAVY OBJECTS October 1 979 2-27 Section ll Limitations BEECHCRAFT Sport lll MusketeerA23-19, 19A PLACARDS (Cont'd) Lower Sidewall Adjacent to Pilot (when installed): -= WARNING G EMERGENCY AIRSPEED STATIC SOURCE sEE FLIGHT MANUAL NORMAL EMERGENcYPRocEDUREs oFF / orv iEMERGENCY FOR AIBSPEEO ALTIMETER CALIBAATION ERROR ,J @ e of o WARNING o EMERGENCY AIBSPEED STATIC SOURCE ON EMERGENCY SEE PILOTS CHECK LIST OR FLIGHT MANUAL EMERGENCY PROCEDURES FOR AIRSPEED & ALTIMETERT CALIBRATION ERROR OFF NORMAL o or @ WARNING @ EMERGENCY AIRSPEED STAIIC SOURCE EMERGENCY ioN I sEE PITOIS CHECK TISI OR FTIGHT MANUAI ENTERGENCY PROCEDURE5 FOR AIRSPEED & ALTIMEIER CATIBRAIION ERROR @ OFF NORMAL o 2-28 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A On Pedestal Between Frant Seats: T---r L_ __ Section ll Limitations loo w N -"1 0 N o s E U P L -l_l October 1 979 2-29 Section ll Limitations BEECHCRAFTSpoTt lll MusketeerA23-19, 19A INTENTIONALLY LEFT BLANK c I BEECHCBAFT Sport lll MusketeerA23-19, 19A SECTION III EMERGENCY PROCEDURES TABLE OF CONTENTS SABJECT Emergency Airspeeds Engine Failure During Take-Off Ground Roll ." ". ".. After Liftoff And ln Flight . Engine Discrepancy Checks Rough Running Engine Loss Of Engine Power Airstart Procedure Engine Fire ln Flight On The Ground Emergency Descent Maximum Glide Configuration Landing Emergencies Landing Without Power Systems Emergencies Alternator-Out Procedure Unscheduled Electric Stabilator Trim Emergency Static Air Source System Unlatched Door ln Flight . Spins. .....".'..:' Entry Spin Recovery . ... PAGE 3-3 3-4 3-4 3-5 3-5 3-6 3-6 3-7 3-7 3-7 3-8 3-8 3-9 3-9 3-10 3-10 3-10 3-1 1 October 1979 3-1 Section lll Emergency Procedures INTENTIONALLY LEFT BLANK BEECHCRAFTSpoTt lll MusketeerA23-19, 19A 3-2 October 1979 BEECHCBAFT Sport llt MusketeerA23-19, 19A Emergency Descent \- Glide . Emergency Landing Approach Seetion lll Emergency Proeedures 132 kts/153 mph . 78 kts/90 mph . 65 kts//S mph All airspeeds quoted in this section are indicated airspeeds (tAS). EMERGENCY AIRSPEEDS Stall warning horn is inoperative when EATTERY & ALT tr-_ switch is turned off. 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 operation of the airplane. Where practicable, the emergencies requiring immediate corrective action are treated in check list form for easy reference and familiari- zation" Other situations, in which more time is usually per- mitted to decide on and execute a plan of action, are discussed at some length. October 1 979 3-3 Section lll Emergency Procedures BEECHCRAFT Sport lll MusketeerA23-19, 19A ENGINE FAItJRE DURING TAKE.OFF GROUND ROLL 1. Throttle - cLosED 2. Braking - MAXIMUM NOTE Conduct the following procedures imme- diately if it appears certain that the airplane will run off the runway. (Otherwise conduct these procedures at the pilot's discretion.) 3. Fuel Selector Valve - OFF 4. BATTERY & ALT, ALT, and FUEL BOOST switches - OFF 5" Magneto/Start Switch - OFF AFI'ER LIFTOFF AND IN FLIGHT 1. Mixture - FULL RICH, then LEAN as required 2. Fuel Boost Pump - ON 3. Fuel Selector Valve - SELECT OTHER TANK (Check to feel detent and check visually) 4. Magnetos - CHECK LEFT and RIGHT, then BOTH NOTE The most probable cause of engine failure would be loss of fuel flow or improper functioning of the ignition system. Landing straight ahead is usually advisable. lf sufficient altitude is available for maneuvoering, accomptish the following: 3-4 October 1979 BEECHCRAFT Sport lll Musketeer A23- 19, 1 9A Section lll Emergency Procedures IF NO REST"ART: 1. Establish maximurn glide 2" Throttle - cLosE 3. Fuel Selector Valve - OFF 4. Mixture - IDLE CUT-OFF 5. Magneto/Start Switch - OFF 6. BATTERY & ALT. ALT, and FUEL BOOST switches - OFF (With electric flaps installed, it will be necessary to set desired flaps before securing battery.) When eertain of reaching the selected landing site 7. Airspeed - 65 ktsf/S mph 8. Flaps - AS REOUIRED ENGINE DISCREPANCY CHECKS CONDfffiN: ROUGH RUNNING ENGINE 1. Mixture - FUtL RICH, then LEAN as required 2. MagnetoTStart Switch - CHECK LEFT and BIGHT, then BOTH CONDITION: IOSS OF ENGTNE PAWER \- 1. Fuel Pressure Gage - CHECK lf fuel flow is abnormally low: a. Mixture - FUtL RICH b. Fuel Boost Pump - ON (Lean as required) c" Fuel Boost Pump - OFF if performance does not improve in a few moments Oetober 1979 3-5 Section lll Emergency Procedures BEECHCRAFT SPort lll MusketeerA23-19, 19A 2. Fuel Ouantity lndicator - CHECK for fuel supply in tank being used lf tank being used is emPtY: a. Fuel Tank-selector Valve - SELECT OTHER FUEL TANK (feel for detent and check visually) b. Fuel Boost PumP - ON AIR START PROCEDURE 1. Fuel Selector Valve - SELECT TANK MORE NEARTY FULL (check to feel detent and check visuaily) 2" ThrOttIC . FULL FORWARD 3" Mixture - FULL RICH 4" Fuel Boost Pump - ON until power is regained, then OFF. (Leave on if engine driven f uel pump is inoperative.) 5. Throttle - ADJUST to desired power 6. Mixture - LEAN as required ENGINE FIRE IN FLIGHT The ventilation controls must be closed to shut off all heat- ing system outlets so that smoke and fumes will not enter the cabin. The control labeled CABIN AIR must be pulled out to close. The control labeled DEFROST must be pushed in to close. ln the event of an engine fire, shut down the engine as follows and make a landing: 3-6 October 1979 BEECHe RAFT Sport lll Musketeer A23- 19, 1 9A Section lll Emergency Procedures 1. Fuel Seleetor Valve - OFF 2. Mixture - IDLE CUT-OFF 3. Throttle - closE 4. Cabin Air Control - pull OFF 5. Defrost Valve - push OFF 6. BATTERY & ALT switch - OFF 7. Magneto/Start S\/itch - OFF 8. Do not attempt to restart engine \ ON THE GROUND 1. Fuel Selector Valve - OFF 2. Throttle - cLosED 3. Mixture - IDLE CUT-OFF 4. BATTERY & ALT and Magnetnptart Switehes - OFF 5. Extinguish with Fire Extinguisher. EMEBGENCY DESCENT l. Throttle - IDLE 2. Airspeed - ESTABLISH 132 kts/153 mph MAXIMUM GLIDE CONFIGUHATION 1. Flaps - UP 2. Airspeed - 78 kts/90 mph Glide distance (Zero Wind Condition) is approximately 1.7 nautical miles (2 statute miles) per 100O feet of altitude above the terrain. October 1979 3-7 Section Ill Emergency Procedures BEECHCRAFT SPort lll Musketeer A23-19, 1 9A LANDING EMERGENCIES LANDING WITHOUT POWER When assured of reaching the landing site selected, and on final approach: 1. Airspeed - 65 ktsfT 5 mph 2. Fuel Selector Valve - OFF 3. Mixture - IDLE CUT-OFF 4. MagnetoPtart Switch - OFF 5. Flaps - AS REOUIRED 6" BATTERY & ALT, ALT, and FUEL BOOST Switches - OFF SYSTEMS EMERGENCIES ALTERNATOR-OUT PROCEDURE' A failure of the alternator will place the entire electrical operation of the airplane on the battery. Alternator failure will be indicated by a discharging or fluctuating ammeter' lf this condition develops, turn the ALT switch to OFF' Turn off all nonessential electrical load to conserve the battery lif e. WARNING Deactivation of the battery/alternator switch, alternator switch, or alternator circuit breaker during flight is prohibited, except as required by an actual emergencY. 3-8 October 1979 BEECHCRAFT Sport ll! MusketeerA23-19, 19A Section lll Emergency Procedures UNSCHEDULED ELECTRIC STABILATOR TRIM 1. Airplane Attitude - MAINTAIN using stabilator eontrol. 2. Stabilator Trim Thumb Switch (On Control Wheel) - MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM to open circuit breaker. 3. Stabilator Trim ON-OFF Switch (On lnstrument panel) - OFF 4. Manual Stabilator Trirh Control Wheel - RETRIM AS DESIRED. \. EMERGENCY STATIC AIR SOURCE SYSTEM THE EMERGENCY STATIC AIR SOURCE SHOULD BE USED FOR CONDITIONS WHERE THE NORMAL STATIC SOURCE HAS BEEN OBSTRUCTED. When the airptane has been exposed to moisture an_d/or icing conditions (especially on the ground), the possibility of obstructed static ports should be considered. Partial obstructions will result in the rate of climb indication being sluggish during a climb or descent. Verification of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of climb. This may be accompanied by abnormal indicated airspeed and altitude changes beyond normal ealibration differences. Whenever any obstruction exists in the Normal Static ,Air System or the Emergency Static Air System is desired for use: 1. Pilot's Emergency Static Air Source - Switch to ON EMERGENCY. 2. For Airspeed Calibration and Altimeter Correetion, refer to PERFORMANCE section. CAUTION Be certain the emergency static air valve is in the NOBIMAL position when system is not needed. October 1979 3-9 Section lll Emergency Procedures BEECHCRAFT SPort lll Musketeer A23-19, 1 9A UNLATCHED DOOR IN FLIGHT lf the cabin door is not locked it may come unlatched in f light. This may occur during or just after take-off ' The door w'iil trail in a position approximately 3 inches open' A buffet may be encountered with the door open in flight' Return to the field in a normal manner' lf practicable' during the landing flare-out have a passenger hold the door to prevent it from swinging open' sPINS (MB-322 thru MB-454) WARNING lntentional spins are prohibited when operating in the Normal Category. lntentional spins are also prohibited in the Utility Category unless the airplane is approved for operation in the Acrobatic Category and has complied with BEECHCRAFT S.l. No. O871-090. The airplane will not spin if brthodox entry is used, but will enter a spiral dive. Speed builds rapidly in a spiral dive, requiring high pullout loads. Therefore, if a spiral is inadvertently entered recovery from the spiral is to be initi- ated within two turns. ENTRY Stall the airplane with the control column hard back,throttle in idle position, flaps up, carburetor heat as required and with the nose about 150 above the horizon' At the stall, apply full rudder in the direction required to spin. A slight rudder application immediately before the 3-1O Octobor 1979 BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Section ll! Emergency Procedures stall will assure the direction of spin. The airplane nose will drop and rotate towards the applied rudder. When the wings are 9Oo to the horizon, apply full aileron againstthe intended direction of spin. The airplane will go slightly inverted and enter a normal spin" ' lf aileron against the directisn of spin is not applied or 'applied too late, the airplane will enter a rapid spiral dive, and recovery must be initiated by the second turn" lf the full back stick is not applied and held, the airplane may spiral. Again recovery must be initiated not later than the second turn. lf aileron is applied tod early, the airplane will not rotate and merely remain in a straight stalled condition. SPIN RECOVERY From spins entered intentionally or inadvertently: lmmediately move the eontrol column full forward and si- multaneously apply full rudder opposite to the direction of \ the spin; continue to hold this eontrol position untll rotation stops and then neutralize all eontrols and exee ute a smooth pullout" Ailerons should be neutral and throttle in idle position at all times during reeovery. October 1979 3-11 Section lll Emergency Procedures INTENTIONALLY LEFT BLANK BEECHCRAFT Sport lll MusketeerA23-19, 19A 3-12 October 1979 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS SUBJECT Speeds for Safe Operation Preflight lnspection Before Starting ... ".. : External Power . Staning Engine Using Auxiliary Power Unit Starting After Starting, And Before Taxi Before Takeoff Takeoff Climb . Cruise " Leaning Using the Exhaust Gas Temperature lndicator Descent Before Landing Balked Landing ,After tandinS ..." Shutdown Environmental Systems Heating and Ventilation ... Cold Weather Operation Preflight lnspeetion Engine leing Conditions .. Engine Break-ln lnformation PAGE 4-3 4-4 4-6 4-6 4-7 4-7 4-8 4-8 4-9 4-14 4-10 4-10 4-11 4-11 4-12 4-12 4-12 4-12 4-12 4-13 4-13 4-13 4-14 4-14 October 1979 4-1 Section lV Normal Procedures INTENTIONALLY LEFT BLANK BEECHCRAFT Sport lll MusketeerA23-19, 19A 4-2 October 1979 All airspeeds quoted in this section are indicated airspeeds \ " i/sl SPEEDS FOR SAFE OPERATION BEECHCRAFTSpoTt lll MusketeerA23-19, 19A Take-off Lift-off 50 Ft. Maximum Climb Best Rate Ny) Best Angle (V*) Cruise Climb Maximum Turbulent Air Penetration Balked Landing o Landing Approach Maximum Demonstrated Crosswind I 6-7 9-10 II 4 2 Seetion lV Normal Procedures 65 Knots[S mph 72 Knots/83 mph 72 Knots,/83 mPh 65 Knots775 mph 89 Knots/100 mph 1 14 Knots/131 mph 58 Knots/67 mph 65 Knots775 mph 13 Knots/l5 rnph 5 Oetober 1979 3 4-3 Section lV Normal Procedures BEECHCRAFT Sport lll MusketeerA23-19, 19A PREFLIGHT INSPECTION Emergency Locator Transmitter - ARMED Location may vary with individual airplanes 1. CABIN: a. Parking Brake - SET b. Control Lock - REMOVE c. All Switches - OFF 2. RIGHT FUSELAGE: a. Static Pressure Button - UNOBSTRUCTED 3" EMPENNAGE: a. Control Surfaees - CHECK b" Tie Down - REMOVE c. Position Light - CHECK 4. LEFT FUSEI-AGE: a. Static Pressure Button - UNOBSTRUCTED b. All Antennas - CHECK 5. LEFT WING TRAILING EDGE:' a. Flap - CHECK b. Fuel Vent Line - UNOBSTRUCTED c. Aileron - CHECK d. Wins Tip - CHECK e. Position Light - CHECK 6. LEFT WING LEADING EDGE: a. Pitot Tube - CHECK, (Remove Cover) b. Landing Light - CHECK c. Tie Down and Chocks - REMOVE d. Stall Warning - CHECK for movement of vane e. Fuel Tank - CHECK OUANTITY; Filler Cap SECURE. 4-4 October 1979 7" LEFT LANDING GEAR: a. Tire and Brake - CHECK b. Fuel Sump - DRAIN 8" /vos6 sECTloN: a. Left Cowl - SECURE b. lnduction Air lntake - CLEAR, Filter - eHECK for condition and security of attachment. c. Propeller - CHECK, General Condition, Nicks, ete" d. Tire and Nose Gear - CHECK e. Engine Oil - CHECK (See Servicing, Section 8) eap and Dipstick - SECURE f. Right Cowl - SECURE g. Fuel Strainer - DRAIN h. Chocks - REMOVE 9. RIGHT LANDING GEAR: a. Fuel Sump - DRAIN b. Tire and Brake - CHECK BEEe HCRAFTSpoTt lll Musketeer A23- 1 9, 1 9A 10, RIGHT WING LEADING EDGE: a. Fuel Tank - CHECK QUANTITY; SECURE b. Tie Down and Chocks - REMOVE c. Wing Tip - CHECK d. Position Light - CHECK Seetion lV Normal Procedures Filler Cap 11. RIGHT WING TRAILING EDGE." a. Aileron - CHECK b. Flap - CHECK c. Fuel Tank Vent Line - UNOBSTRUCTED October 1979 4-5 Section lV Normal Procedures BEECHCRAFT Sport lll Musketeer A23-1 9, 19A BEFORE STARTING 1. Seats - POSITION AND LOCK; Seat Backs - UPRIGHT 2. Seat Belts and Shoulder Harnesses - FASTEN 3. Parking Brake - SET 4. All Avionics -'.OFF 5. Circuit Breakers - lN 6. Flaps - UP 7. Light Switches - AS REOUIRED 8. Electric Stabilator Trim Switch - OFF (if installed) 9. BATTEBY & ALT Switch - ON 10. ALT Switch - ON (lf external power is used, turn ALT Switch - OFF) 'l 1. Fuel Boost Pump - ON (Check for operation, then OFF) 12. Fuel Selector - ROTATE thru 36O0 and check for free- dom of movement, set on tank more nearly full (feel for detent and check visually) WARNING Do not take off if gages indicate in yellow arc on either gage (airplanes after compliance with BEECHCRAFT S.l. No. 0624-281). EXTERNAL POWER The following precautions shall be observed while using \.. external power: 1. The Battery Switch shall be ON and all avionics and electrical switches OFF. This protects the voltage reg- ulators and associated electrical equipment from volt- age transients (power fluctuations): 2. The airplane has a negative ground system. Connect the positive and negative leads of the external power unit to the corresponding positive and negative terminals of the airplane's external power receptacle.' - 3. ln order to prevent arcing, no power shall be supplied while the connection is being made. 4-6 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Section lV l\lorrnal Proeedures STARTING ENGINE USING AUXILIARY POWER UNIT 'l . Alternator, Eleetrical, and Avionics Equipment - OFF 2. Auxiliary Power Unit - CONNECT 3" Auxiliary Power Llnit - sET oUTPUT (13"75 to 14"25 volts) \ 4. Auxiliary Power [-lnit ON \- 5. Engine - START using normal procedures 6. Auxiliary Power Unit - OFF (after engine has been started) 7. Auxiliary Power Unit - DISCONNECT 8. Alternator Switch - ON STARTING CAUTION Vernier-type engine controls should not be rotated cloekwise after being advanced to the full forward position. 1. Mixture - FULt RICH 2. Throttle - FAST IDLE position 3. Fuel Boost Pump - ON (cold weather starts. use one to six strokes of engine prime, as required) CAATION Starter cranking period should be limited to a maximum of 3O seconds, with at least 2 minutes between cranking periods. 4. MagnetoBtart Switch - START Bositian (release to BOTH position when engine fires) CAUTION DO NOT FUNilP THROTTLE TO START October 1979 4-7 Section lV Normal Procedures BEECHCRAFT Sport lll MusketeerA23-19, 19A Flooded Engine: a. Mixture - IDLE CUT-OFF b. Throttle - FULL OPEN c. Starter - ENGAGE (retard throttle to fast idle when engine fires) d. Mixture - ADVANCE TO FULL RICH 5. External Power (if used) - OFF - DISCONNECT 6. ALT (alternator) Switch - ON 7" Oil Pressure - ABOVE RED RADIAL WITHIN 30 SECONDS 8. Warm-up - 800 to 120O RPM 9. Engine lnstruments - CHECK 10. Throttle - 1500 RPM 1 1. Ammeter - CHECK EAUTION Charge indication should begin to decrease within 2 minutes after engine start and should be within 1/4 scale of zero prior to takeoff. lf not, an electrical ditficulty is indicated. and the airplane should be shut down. 12. Throttle - IDLE 13. Fuel Boost Pump - OFF (for test of engine driven pump, then ON) AFTER STARTING, AND BEFORE TAXI 1. Parking Brakes - RELEASE 2. Brakes - RELEASE AND CHECK 3. Avionics Equipment - ON, AS REOUIRED 4. tights - AS REOUIRED BEFORE TAKEOFF 1. Parking Brake - SET 2. Seat Belts and Shoulder Harnesses - CHECK 4-A October 1 979 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A Section lV Normal Procedures NOTE All reclining seats must be in the upright posi- tion during take-off. 3. Avionics - CHECK 4. Engine lnstrurnents - CHECK 5. Flight lnstruments - cHEcK AND SET 6. Throttle - 2OOO RPM 7. Magnetos - CHECK at 2OOO rpm, maximum drop of 125 rpm on each magneto. variance between indi- vidual magnetos should not exceed 5O rpm. 8. Carburetor Heat - CHECK (Set eold for takeoff) 9. Throttle - 15OO BPM 10. Ammeter - CHECK for stabilized indication within 1/4 scale of zero 11" Throttle - FAST IDL€ 12. Stabilator Trim - TAKE-OFF RANGE (Green Band) 13. Flaps - eHEeK and SET 14" Controls - CHECK FREE and for proper direction of travel 15. Fuel Boost Pump - CHECK ON 16. Mixture - FULL RICH (or as required by field elevation) (tighten friction on push-pull type eontrol) 17. Doors and Window - SECURE 18. Parking Brake - RELEASE 19" lnstruments - CHECK (engine instrumeRts in green range at the start of the take-off run) TAKEOFF Takeoff ". Full Throttle 1. Power - SET takeoff power and mixture before brake release. 2. Airspeed - ACCELERATE to and maintain take-off speed" 3. Airspeed - ESTABLISH DESIRED CLIMB SPEED when clear of obstaeles. october 1979 4-9 Section lV Normal Procedures BEECHCRAFTSpoTt lll Musketeer A23-1 9, 1 9A CLIMB NOTE Do not turn Fuel Boost Pump off during climb. 1. ThrOttIE - FULL FORWARD 2. Temperature ;. I$ONITOR 3. Mixture - LEAN AS REOUIRED FOR SMOOTH OPERATION CRUTSE I " Power - SET AS DESIRED (Use tables in PER- FORMANCE Section) 2. Fuel Boost Pump - OFF 3. Mixture - LEAN AS REOUIRED (tighten friction on push-pull type control) LEANING USING THE EXHAUST GAS TEMPERATURE INDICATOR (EGT) For level flight at 75o/o powet or less, the EGT unit should be used in the following manner: tean the mixture and note the point on the indicator that the temperature peaks and starts to fall. a. CRUISE (LEAN) MIXIURE - Enrich mixture until the EGT shows a drop of 25oF below peak on the rich side of peak. b. BEST POWER MIXfURE - Enrich mixture until the EGT shows a drop of 75oF below peak on the rich side of peak. CAUTION Do not continue to lean mixture beyond that necessary to establish peak temperature. 2" Continuous operation is recommended at 25oF or more below peak EGT only on the rich side of peak. 4-10 October 1979 BEECHGRAFT Sport Ill Musketeer A23- 19, 1 9A Section lV Normal Procedures 3. Changes in altitude and power settings require the peak EGT to be rechecked and the mixture reset. DESCENT 1. Altimeter - SET. 2" Carburetor Heat - WHEN REOUIRED. 3. Power - AS REOUIRED (avoid prolonged idle settings which may cause low cylinder head temperatures). 4" Mixture - ENRICH AS REOUIRED" BEFORE LANDING 1" Seat Belts and Shoulder Harnesses - SECURE. NOTE All reclining seAts must be in the upright position during landing. 2. Fuel Seleetor Valve - SELECT TANK MORE NEARLY FULL (feel for detent and check visually). 3. Mixture - FUIL RICH (or as reguired by field elevation) (tighten frietion on push-pull type control) 4" Landing Light - AS REOUIRED 5. Flaps - DOWN (rnaximum extension speed, 97 kts/1 1 1 mph) NOTE The Flaps Up landing procedure will increase the Flaps Down landing distances (total over 5O foot obstaele) by 5O7o. 6. Airspeed - ESTABLISH tlNDtNG APPROACH SPEED Flaps Down - 65 kts775 mph 7" Carburetor Heat - AS REOUIRED NOTE Carburetor heat should be in the full COLD (lN) position before f ull throttle applieation in the event of a go-around. 8. Fuel Boost Pump - ON October 1979 4-11 Section lV Normal Procedures BEECHCRAFT SPort lll MusketeerA23-19, 19A BALKED LANDING 1. Carburetor Heat - COLD 2. Power - FULL THROTTLE 3" Airspeed - 58 kts/67 mph until clear of obstacles, then triM tO BEST RATE.OF-CLIMB 4. Flaps - UP AFTER LANDING 1" Landing Light - AS REOUIRED 2. Flaps - UP 3. Trim Tab - SET TO 0o SHUTDOWN 1. Brakes - SET 2. Fuel Boost PumP - OFF 3. Electrical and Avionics Equipment - OFF 4. Throttle - cLosE 5. Mixture - IDLE CUT-OFF '6. Magneto6tart Switch - OFF, after engine stops 7. BATTERY & ALT Switch - OFF 8. ALT Switch - OFF 9. Control Lock ' INSTALL, if conditions warrant' 1O. lnstall wheel chocks and release brakes if the airplane is to be left unattended. ENVIRONMENTAL SYSTEMS HEATING AND VENTILATION Refer to the SYSTEMS DESCRIPTION Section for op- eration of heating and ventilation controls. 4-12 october 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Seetion lV Normal Procedures COLD WEATHER OPERATION PREFLIGHT INSPECTION All accumulations of ice, snow and frost must be rernoved from the wings, tail, control surfaces and hinges, pro- peller, windshield, pitot tube, static ports, anteRnas, fuel cell filler caps, crankcase vents, and fuel vents. lf such accumulations are not removed completely, the airplane shall not be flown. The deposits will not blow off in f light. While an adverse weight {actor is clearly involved in the case of heavy deposits, it is less obvious that even slight accumulations will disturb or completely destroy the de- signed aerodynamic properties cf the airfoils. 'fhe normal preflight 'procedures should then be ccm- pleted, with particular attention given to check of flight eontrols for complete freedom of movement. ENGINE Use engine oil in accordance with Consumable Materials in the HANDLING, SERVICING AND MAINTENANCE Section. WARNING Ascertain that magneto switch and battery 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 "lirnber up" the cold, heavy oil before using the starter. This will also lessen the load on the.battery if external power is not used. During cold weather stans, use 1 to 6 strokes of engine primer, as required. CAUT!ON Do not pump throttle to start October 1979 4-13 Section lV Normal Procedures BEECHCRAFT SPort lll Musketeer A23- 1 9, 1 9A Under very cold conditions, it may be necessary to preheat the engine prior to a start. Particular attention should be given to the oil cooler and engine sump to ensure proper preheat. A start with congealed oil in the system may pro- duce an indication o{ normal pressure immediately after the start. but then the oil pressure may decrease when re- sidual oil in the engine is pumped back with the con- gealed oil in the sump. lf an engine heater capable of heat- ing Uotn the engine sump and cooler is not available' the oil-should be drained while the engine is hot and stored in a warm area until the next flight. lf there is no oil pressure within the first 30 seconds of running, or if oil pressure drops after a few minutes of grornd operation, shut down and check for broken oil iines, oil cooler leaks or the possibility of congealed oil' NOTE It is advisable to use external power for start- ing 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' During letdown and landing. give special attention to en- gine temperatures, since the engine will have a tendency toward overcooling. ICING CONDITIONS Flight in Known lcing Conditions Prohibited. ENGINE BREAK.IN !NFORMATION See Systems DescriPtion section 4-14 October 1979 BEECHCRAFT Sport lll Musketeer A23- 19, 1 9A SECTION V PERFORMANCE TABLE OF CONTENTS SUBJECT lntroduction to Performance and Flight Planning "" " eomments Pertinent to the Use of Performance Charts Airspeed Calibration - Normal System Airspeed Calibration - Alternate System Altimeter Correction - Normal System Altimeter Correction - Alternate System Power Off Stall Speeds Wind Components . Take-Off Distanee - 22@ Take-Off Distance - 2250 Rate-of-Climb .. " " Cruise Performance Landing Distance PAGE October 1979 5-1 I 5-3 ........ 5-7 . ". ".... 5-8 .."..... 5-9 .".".". 5-10 """".". 5"11 5-12 ...... 5-13 "... .. 5-14 . 5-15 . 5-16 5-17,5-18 5-19 Section V Perf ormance BEECHCRAFT Sport lll MusketeerA23-19, 194 INTENTIONALLY LEFT BLANK { OrO BEECHCRAFTSpon lll MusketeerA23-19, 19A Section V Performance 1 soc (59oF) 5330 ft .. 29.60 in. Hg 27Ao at 10 kts ..... 10,010 ft INTRODUCTION TO PERFORMANCE AIND FLIGHT PLANNING Alt airspeeds quoted in this section are indicated air' speeds (IAS) except as noted and assume zero instrument error. The graphs and tables in this section present performance information for flight planning at various parameters of weight, power, altitude and temperature. Examples have been presented on some performance charts. Calcula- tions for flight time, block speed and fuel required for a sample VFR trip from Denver to Wichita are detailed below. All examples and calculations assume the following conditions: CONDITIONS At Denver: Outside Air Temperature .. " ".... Field Elevation .. ". Altimeter Setting Wind Runway 26L length Route of Trip *DEN-V4.GLD.Vl 32-HUT.V73-ICT For VFR Cruise at 9,5O0 feet "REFERENCE: Enroule Low Altitude Chart L-6 ROUTE SEGMENT MAGNETIC COURSE DIST NM WIND 9500 FEET DrR/KTS OAT 9500 FEET oc ALT SETTING IN.HG DEN.TXC TXC.GLD GLD-HUT HUT.ICT 0900 0920 1020 1 160 72 73 194 28 01a/,zo 01o/2o 220/1O 220/1O -4 -4 5 1 29.60 29.60 29.56 29.56 October 1979 5-3 Section V Performance At Wichita: Outside Air Temperature Field Elevation ........ Altimeter Setting Wind .?....... Bunway 19 Length BEECHCRAFT Sport lll MusketeerA23-'l 9, 19A . 25oC (77cF, 1332 f: . 29.56 in. Hg 1800 at 10 kts 7301 ft To determine pressure altitude at origin and destination airports, add 1OO feet to field elevation for each.1 in. Hg below 29.92, and subtract 100 feet from f ield 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 f ield elevation. 5330 + 320 = 5650 ft Pressure Altitude at ICT: 29.92 - 29.56 = .36 in. Hg The pressure altitude at ICT is 360 feet above the f ield elevation. 1332+360=1692ft NOTE For flight planning, the difference bewveen cruise altitude and cruise pressure altitude has been ignored. 6-L f'lnfnlrar 1Q7Q BEECHCBAFT Sport lll MusketeerA23-19, 19A Section V Performanee Enter the CRUISE PERFORMANCE table for 2600 RPiM at 9500 feet: ALTITUDE FEET THROTTLE SETTING RPM FUEt FtOW GPH TAS KT\IOTS 9500 2600 8.3 111 Time and fuel used wqre caleulated as follows Time = Distanee Ground Speed Fuel Used = 6ime) (Fuel Flow) Results are BOUTE SEGMENT DISTANCE NM EST GROUND SPEED KNOTS TIME AT CRUISE ALTITUDE HRS: MIN FUEL USED FOR ERUISE GAL DEN.TXC TXC.GLD GLD-HUT HUT-ICT 72 73 194 28 108 108 116 113 O:40 O:41 1:40 O:15 5.5 5.6 13"9 ?.1 October 1979 5-5 Section V Perf ormance BEECHCRAFT Sport lll MusketeerA23-19, 19A TIME . FUEL. DISTANCE Total Flight Time: 3 hours, 16 minutes BlockSpeed: 367 NM + 3 hours" 16 minutes = .l12 knots Reserve Fuei (45 minutes at 2300 RPM, 9500 feet) Enter the CRUISE PERFORMANCE table for 9500 feet and obtain fuel flow at 2300 RPM. The fuel f low is 6.2 gallons per hour. Reserve 1u"1 = (45 min) (6.2 GPH) = 4.7 gallons Total Fuel = 28.0 + 4.7 = 32.7 gallons The estimated landing weight is determined by subtracting the fuel required for the trip from the ramp weight: Assumed ramp weight = 22O5 lbs Estimated fuel from DEN to ICT = (28.O 9al)(6 lbs/gal) = \- 168 lbs Estimated landing weight = 2205 - 168 = 2037 lbs ITEM TIME HRS: MINS FUEL GAL DISTANCE NM Stan, Runup, Taxi and Take- off acceleration Cru ise Total C:OO 3: 16 J: tb o.9 27.1 28.O o 367 367 6-6 Aa+a!.a. O7O BEEGHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Section V Perforrnance COMMENTS PERTINENT TO THE USE OF PERFORMANCE CHARTS The example, in addition to presenting an answer for a particular set of conditions, also presents the order in which the charts should normally be used, i.e., if the f irst item in the example is OAT, then enter the chart at the known OAT. 2. lndicated airspeeds (lAS) were obtained by using the AIRSPEED CALIBRATION NORMAT SYSTEM ChaTt. 3. The associated conditions define the speeific conditions from which performance parameters have been determined. Tfiey are not intended to be used as instructions, however, performance values de- termined from charts can only be achieved if specified conditions exist" 4. The full amount of usable fuel is available for all approved flight conditions. 5" Engine and eomponent cooling has been demon- strated for temperatures up to 1OOuF at sea level with a 3.67"F per 10OO ft lapse rate. (lSA + 41uF) October 1979 5-7 gr @ AIRSPEED CALIBRATION - NORMAL SYSTEM 46 52 58 63 69 81 86 92 98 104 't09 115 121 127 132 138 144 150 TOoo 19!o 3r 3<o o 48 54 59 64 70 75 79 84 90 95 101 107 75 F, *HoO o.rgl o kiP{JO (o! o1D= oo oq o (o (o l123.r "', I \_ IND!CATED AIRSPEED CALIBRATED AIRSPEED KNOTS MPH U KN 58 oz 66 70 75 80 85 90 95 100 106 111 116 x20 't24 128 67 71 76 81 86 92 98 104 109 115 122 128 133 138 143 147 FLAPS DOWN KNOTS MPH 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 't15 120 125 130 42 47 51 56 61 65 69 73 78 83 B8 93 MPH AIRSPEED CALIBRATION - AI-TERIVATE SYSTEM ..-- =HAm [9qs NTur- t. ul FE (o= oo o oo (o (o To irjso=' 8?gr (o STORM WINDOW CLOSED STORM WTNDOW OPEN FLAPS UP FLAPS DOWN FLAPS UP FLAPS DOWN IAS (MPH) tAs (MPH) tAs (MPH} IAS (MPH} IAS (MPH} 7A 80 90 100 110 120 130 140 1sCI v5 86 96 147 117 127 138 148 158 74 84 94 105 115 80 90 11'[ 121 132 142 152 162 79 89 99 109 '!19 823-KCt-10 qI o ALTIMETEB CORRECTION - NORMAL SYSTEM aooo 19io Jro< o o 40 45 50 55 60 65 70 75 80 85 90 95 100 105 110 11 I 6 5 4 2 .3 11 17 20 Fo SHoO O.! E9 EiPi)Ul(0E 'o @1 D= oo 0 cr o (o {(o 82? 11 INDICATED AIRSPEED KNOTS MPH ALTIMETE R CORBECTION TO BE ADDED - FEET FLAPS UP FLAPS DOWN SL 10000 FT SL 10000 FT 46 52 58 63 69 75 81 86 92 98 104 109 115 121 127 10 I 6 2 -4 -5 -4 -2 1 4 7 14 12 I 6 -3 -4 -3 0 3 6 I I 7 5 4 J 1 -6 -17 -23 -26 ! \-- ALTTMETEH COBRECTION \- ALTERNATE SYSTEM FH6m il9 q9 N .TI or- ,- lh -68 G'= oo og o (o (o i{ ,' E o lrnYo .io5d P6' 8z U'I I STORM WINDOW. CLOSED STORM WINDOW. OPEN rAs (MPH) FLAPS UP (FEET} FLAPS DOWN (FEET) FLAPS UP (FEETI FLAPS DOWN (FEET} 7A 80 g0 100 110 120 130 140 't50 20 30 40 50 60 7A 75 85 20 ,tr 30 35 40 45 60 70 85 95 110 124 't35 150 40 50 60 70 80 823-KCl.12 Section V Performance BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A POWER OFF STALL SPEEDS \ (wEtGHT 22OO LBS) Maximum altitude loss during a normal stall recovery is approximately 3OO ft. ANGLE OF BANK LEVEL 300 450 600 FLAPS-UP 67 mph 58 kts 72 mph 63 kts 81 mph 70 kts 99 mph 86 kts FLAPS - DOWN (35o) 55 mph 48 kts 60 mph 53 kts 67 mph 58 kts 82 mph 71 kts (wElGHT 2250 LBS) Maximum altitude loss during a pormal stall recovery is approximately 30O ft. ANGLE OF BANK LEVEL 300 450 600 FLAPS-UP 68 mph 59 kts 74 mph 64 kts 83 mph 72 kts 1O1 mph 88 kts FLAPS - DOWN (35o) 56 mph 49 kts 62 mph 54 kts 68 mph 59 kts 84 mph 73 kts 5-12 October 1 979 7_ BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Section V Performance HEADWIND COI{PONENI CROSSWIND COMPONENT TIIGHI PATH WIND COMPONENTS Demonstroted Crosswind is I3KTS/I5MPH EXAMPTE: WIND SPEED 15 KTs ANGTI BEIWEEN WIND DIRECTION AND TTIGHT PATH 5O' IO KTS II KI5 40 20 lo 30 o z I z z o {o o =, o I o _to o F 40 October 1 979 10 20 cRosswrNo col PoNtNT - 30 KNOTS 5-13 o aooo *3.xo 3ro<)o o ol 5 TAKE.OFF DISTANCE 22oO LBS ASSOCIATED CONDITIONS POWER FULLTHROTT LE EXAMPLE OAT PRESSUBE ALTITUDE I-IEADWIND GROUND ROLL TOTAL DISTANCE 150F 4OOO FEET 1O KNOTS 959 FEET 1696 FEET FLAPS BUNWAY WEIGHT UP LEVEL, DRY, PAVED SURFACE 22OO POUNDS 5o IHiD() o+oo KE Pi)g)(o1, 'o Jl (o- D= oo o cr o @ (o Sea Level 2000 Ft, 4000 Ft" 6000 Ft. 8000 Ft, Wind Vel KTS Oat Fo Grnd Run Ft. lo Clear 50' Obst Ft. Oat Fo Grnd Run Ft. To Clear 50' obn Ft. Oat Fo Grnd Run Ft. lo Clear 50' Obst Ft. Oat Fo Grnd Run Ft. To Clear 50' Obst Ft. Oat Fo Grnd Run Ft. To Clear 50' Obst Ft. -10 30 59 90 1 133 1371 1 703 1940 2412 2838 20 52 80 1276 1 608 1987 2246 2706 3*4s 15 45 75 1 499 1 864 2317 2553 3142 3184 10 38 70 17 13 21 66 2744 3004 3689 4070 0 30 60 2024 2601 3180 3547 4257 5202 0 30 59 90 777 984 1219 't392 1 730 2104 20 52 80 902 1 147 1424 1604 2000 2439 15 45 75 1052 1344 1672 1 857 2323 2843 10 3B 70 1 235 1 581 1972 2161 2714 3331 0 30 60 't461 1878 2350 2541 3203 3943 10 30 59 90 703 895 1 109 1272 1573 1929 20 52 80 815 1045 1 303 1464 1835 2238 't5 45 75 959 1227 1294 1696 2139 2609 10 38 70 11 14 1449 1812 1987 2503 3072 0 30 60 1 328 17 15 2166 2337 2405 3628 30 30 59 90 5s6 718 889 1 031 1258 1 580 20 52 80 642 841 059 1 1 183 1 505 1 836 15 45 75 770 993 I 206 1372 1 769 2147 10 38 70 474 1 183 1 490 1 637 208 1 2553 0 30 60 1 059 1 391 1 798 1930 2412 2999 NOTE: Minus sign indicates tailwind A23-19-KCr-1 =H Arfi -C) o- Q9 N'r! (, -l tub .6: (lr = oo o lro J (o {(, TAKE.OFF OISTANCE 2250 LBS ASSOCIATED CONDITIONS POWEB FULLTHROTT LE EXAMPI.E OAT PRESSURE ALTITUDE HEADWIND GROUND BOLL TOTAL DISTANCE I boF 4OOO FEET 1O KNOTS 1014 FEET 1792 FEET FLAPS RUNWAY WEIGHT UP LEVEL, DRV, PAVED SURFACE 2250 POUNDS ffi) ql (r1 !o 1rieE6' f,-, o< Soa Levol 2000 Fr 4000 Ft. 600O Ft. 8000 Ft. Wind Vel KTS Oat Fo Grnd Run Ft. To Clear 50' Obst Ft. Oat Fo Grnd Run Ft. To Clear 50' Obst Ft, Oat Fo Grnd Run Ft. To Clear 50- Obst Ft. Oat Fo Grnd Flun Ft. To Clear 50' Obst Ft. Oat Fo Grnd Run Ft. To Clear 50' Obst Ft. -10 30 59 90 1 200 x 450 1800 2050 2550 3000 20 52 80 1 350 1 700 2100 2375 2860 3640 15 45 75 1585 1 970 2450 2700 3320 4000 10 38 70 1810 2290 2900 31 75 3300 4300 0 30 60 2140 2750 3360 3750 4500 5500 0 30 59 90 ,422 041 288 1 t 't 471 1 828 2224 20 52 80 954 1212 1 505 1 695 2114 2579 15 45 15 1113 1420 1767 1963 2456 3005 10 38 70 1 305 1671 2085 2285 2869 3521 0 3o 60 't544 1985 2485 26a7 3386 4168 10 30 59 9o 74s 947 1172 1344 '! 662 2039 20 52 BO 836 1 105 1377 1547 1939 2366 '!5 45 75 101 4 1297 1614 't792 2261 27@ 't0 38 70 1178 1 531 1915 2100 2646 3247 0 30 60 1 403 1813 22gO 2471 3270 3835 30 30 EO 90 590 760 940 1 090 1 330 1 670 20 52 80 680 890 't120 1250 1590 1940 15 45 75 815 1 050 't275 1450 1870 2270 10 38 70 92s 1250 1 575 1 730 2200 2'too 0 30 60 1120 1470 1900 2040 2550 31 70 NOTE: Minus sign indicates tailwind. 19A-KCt-1 Section V Performance RATE.OFCLIMB ASSOCIATED CONDITIO NS: POWER FLAPS MIXTUBE EXAMPLE_i WEIGHT PRESSUBE ALTITUDE BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A FULL THROTILE UP FULL RICH 2OOO LBS 4000 FT CLIMB SPEED RATE.OF.CLIMB 7Ol81 KTS/MPH 708 FT/MIN WEIGHT LBS PRESSURE ALTITUOE FT CLIMB SPEED KNOTS/MPI{ RATE OF CLIMB- FTIMIN 2250 SL zno0 8000 12000 741A5 73184 70181 69/80 700 485 270 55 2200 SL 4000 8000 1 2000 74185 73184 70181 69/80 740 52s 310 95 2000 SL 4000 8000 1 2000 72183 70/B 1 69/79 68178 935 708 482 258 1 800 SL 4000 8000 1 2000 69iBO 70181 69/79 66/76 1 167 925 685 448 19A-KCl-2 5-16 October 1979 CRUISE PERFOBMANCE STANDARD DAY 38.8 GALLONS 2s00 3500 NOTE: Cruise performance is based on best power mixture" Lean to maximum RPM for best performance. BEECHCRAFT Sport !ll MusketeerA23-19, 19A Section V Performance (, -: o Y O) October '1979 ALT RPM %BHP FUEL FLOW ry GPH TRUE AI RSPEED KTS/MPH ENDUR. ANCE HOURS RANGE S. MILES 2500 23sO 2200 75 63 53 9.0 7.6 6.5 1101126 101/1 16 93/1 07 3.7 4.4 A' 469 5 tJ 559 2525 2400 2250 75 65 55 9.0 7"8 6.7 111 1127 103i1 19 96/1 10 3.7 4.3 5.0 470 507 546 4500 2550 2400 2250 75 63 53 9.0 7"6 6n5 111 1128 103/1 18 95/1 09 3.7 4.4 5.2 472 515 564 5500 2600 2450 2300 77 65 55 9.2 7.8 6.7 1141't31 1051121 97 1112 3.7 4.3 5.0 468 512 551 6500 2600 2450 2800 75 63 il 9.O 7.6 6.6 113/130 1041120 97 1111 3.7 4"4 5.1 475 519 556 7500 2600 2450 2300 73 62 53 8.8 7.4 6.5 't 121129 103/119 97 1'.t11 3.8 4.4 5.4 481 519 564 8500 2600 2450 2300 71 60 52 8.5 7.2 6.4 1111128 1021117 96/1 1 0 4.0 4"6 5.2 488 522 5& 9500 2800 2450 2300 69 59 51 8.3 7.1 6.2 111 1127 107 1117 9511 09 4.1 4.7 5.3 500 537 572 1 0500 2550 2450 2300 63 57 50 7.6 6.9 6.1 1061122 101i 1 16 94/1 08 4.4 4.8 5.3 521 545 573 5-17 Section V Perf ormance BEECHCRAFTSpoTt lll MusketeerA23-19, 19A CRUISE PERFORMANCE STANDARD DAY 58.8 GALLONS RANGE S. MILES 789 845 913 NOTE: Cruise performance is based on best power mixture. Lean to maximum RPM for best performance. October 1979 ALT RPM %BIIP FUEL FLOW - GPH TRUE AI RSPEED KTS/MPH ENDUR. ANCE HOURS 2500 2500 2350 2200 75 63 53 9.0 7.6 6.5 1101126 101/1 16 93/1 07 6.O 7.1 8.4 749 o lo 894 3500 2525 2400 2250 75 65 55 9.0 7.8 6.7 1111127 103/1 19 96/1 10 6.0 6.9 8.0 /5 t otJ 874 4500 2550 2400 2250 75 63 53 9.0 7.6 6.5 111 1128 103/118 95/1 09 6.0 7.O 9.3 7s6 827 90s 5500 2600 2450 2300 77 65 55 9.2 7.8 6.7 1 141131 1051121 97 11 12 5.8 6.8 8.0 752 823 887 6500 2600 2450 2800 75 63 54 9.0 7.6 6.6 113/130 '1041120 97 1111 5.9 54 8.1 763 836 897 7500 2600 2450 2300 73 62 53 8.8 7.4 6.5 1121129 103/1 19 97 1111 6"1 7.1 8.3 775 838 910 8500 2600 2450 2300 71 60 R) 8.5 7.2 6.4 111 l12B 10211 17 95/1 1 0 6.3 7.3 8.4 9500 2800 2450 2300 69 EO 51 o.J 7.1 6.2 111 1127 107 1117 95/1 09 6.5 7.5 8.5 806 Bbb or? 1 0500 2550 2450 2300 63 57 50 7.6 6.9 b. I 1061122 101/1 16 94/1 08 6.7 7.7 8.6 843 882 928 5-18 >- =HAm qE ono- N.T [J -'l a- Cn 6E -A Gr= oo 0(t o (o (o !o i!. ta Yo -io =d96' 8i (, (o LANDING DISTANCE EXAMPLEi WEIGHT OUTSIDE AIR TEMPERATURE PRESSURE ALTITUDE HEADWINO COMPONENIT POWEB GROUND ROLL TOTAL OVER 50 FT OBSTACLE APPROACH SPEED NOTE: 1. DECREASE DISTANCES4% FOB EACH 5 KNOTS HEADWIND' FOB OPERATIONSWITH TAILWINDS UPTO IO KNOTS, INCBEASE OISTANCES BY 9% FOR EACH 2.5 KNOTS. RETARDED TO MAiNTAIN 5OO FTl[4IN ON FINAL APPROACI-I 100% PAVEO, LEVEL, DRY SURFACE MAXIMUM 22OO POUNDS looc 4OOO FEET ,IO KNOTS FLAPS RUNWAY BBAKING T\ UE- ;€ .v i\. 1q, /ft 688 FT 2't60 FT 65 KNOTS/75 MPH SPEED AT 50 FT KNOTS/ MPH SPEED AT CONTACT KNOTS/ MPH' PRESS ALT FEET ooc 100c 20oc 30oc 40o GROUND ROI.L TOTAL TO CLEAR 50 FT OBS GBOUND ROLI. TOTAL TO CLEAR 50 FT OBS GROUND ROLL TOTAL TO CI.EAR 50 FT O8S GROUND ROLL TOTAL TO CLEAR 50 FT OBS GBOUND ROLL TOTAL TO CLEAR 50 FT OBS 65175 54162 SL 2000 4000 6000 8000 r 0000 543 616 701 8't5 922 1066 1 793 1995 2224 2493 2809 31 83 578 748 856 986 141 1 .l892 2102 2348 2636 2976 3377 6r3 657 796 914 1053 1219 1988 2213 2477 2756 3t48 3577 650 741 846 972 1121 1 299 2088 2328 261 0 2940 3327 3784 694 785 898 '1033 I 193 1380 2191 2447 2746 3098 3510 3890 19A.KCl.5 ASSOCIATED CONDITIONS: Section V Performanee INTEI\TIONALLY LEFT BLANK BEECHCRAFT Sport lll MusketeerA23-19. 19A s-20 October 1979 BEECHCBAFT Sport lll Musketeer A23- 1 9, 1 9A SECTION VI WEIGHT AND BALANCE/ EOUIPMENT LIST TABLE OF CONTENTS SUBJECT PAGE lntroduction to Weight and Balance ". . . Weighing lnstructions 6.. . ". . Schematlc Sample - Basic EMPTY Weight and Balance Form . 6-7 Weight and Balanee Record 6-9 Weight and Balance Responsibilities 6-1 1 Gross Weight Moment Limits . 6-12 - 6-14 Computing Procedure 6-15 Sample Weight and Balance Loading Form 6-16 Weight and Balance Loading Form " 6-17 Useful Load Weights and Moments .. 6-18 Occupants 6-1 I oit .." 6_19 Usable Fuel . 6_1 g Baggage 6-2C Equipment List " . Provided for Each Airplane 6-3 6-4 6-6 October 'l 979 5-1 Section Vl Wtand BalzEquip List INTENTIONALLY LEFT BLANK BEECHCRAFT Sport lll MusketeerA23-19, 19A 6-2 October 1979 BEECHCRAFTSpoTt lll Musketeer A23- 1 9, 1 9A Section Vl Wt and BaluEquip List INTRODUCTION TO WEIGHT AND BALANCE The necessity for proper computation of the airplane's weight and balance cannot be overemphasized. ln the basic design, it is planned that under normal loading the , weight distribution of pilot, passengers, baggage, and fuel L will balance the airplane for flight. Since these items are all variables, it is possible to concentrate weight in such a way as to make the airplane unsafe for flight. The factors which must be considered in the weight and balance of the . airplane are the installation of equipment after the air- L plane has been weighed, trapped or unusable fuel, engine oil, usable fuel, pilot and passenger weights. and baggage or cargo" ln order to simplify the computation of the weight and balance, Beech Aircraft Corporation has devised a form called Basic Empty Weight and Balance. When the air- plane is delivered from the factory it will first be weighed and the data recorded on this form. Provision has been made on the form for listing additions of items to be installed before the delivery or subtractions of items to be removed before delivery from the "as weighed" condition. This then represents the empty weight of the airplane. When the airplane is first fueled, a certain amount of fuel is trapped in the fuel lines and cells which cannot be drained. Also, in some regimes of flight there are certain amounts of fuel that cannot be used. The combination of \ these fuel amounts is classified as unusable fuel. Also, it has been found that all operators bring the oil level near full before each flight. Thus, these "items are computed along with the empty weight. giving a Basic Empty Weight as a starting point to the pilot for each f light computation. Once the Basic Empty Weight for a given airplane has been established, the pilot is then only concerned with the Oetober 1 979 6-3 Section Vl Wt and BaLEquip List BEECHCRAFTSpoTt lll Musketeer A23-1 9, 1 9A variable items which will comprise his useful load. These - items which are of a changing nature are: Pilot and Passengers (computed on an individual weight and the seat occupied), Baggage and/or Cargo (computed on weight and locatibn'within the airplane), and Usable Fuel (the remaining fuel after subtracting the unusable fuel r- from the measured fuel on board). WEIGHI NG I NSTRUCTIOI!S Periodic weighing of the airplane may be required to keep '- the Basic Empty Weight current. All changes to the airplane affecting weight and balance are the responsibility of the airplane's operator. Provision for jack points are provided for weighing: two on the wing front spar at Fuselage Station 129.4 and one on the aft fuselage at Fuselage Station 285.9 (tail tie-down ring). 2. Fuel should be drained preparatory to weighing. Tanks are drained from the regular drain ports with the airplane in static ground attitude. The unusable fuel to be added to a Basic Empty Weight is: 6 lbs at Fuselage '- Station 125.0. 45.6 lbs (airplanes after compliance with Service lnstructions No. 0624-281) at Fuselage Station 125.O. 3. Engine oil must be at the full level or completely r- drained. Total engine oil when full is'l 5 pounds at. Fuselage Station 48. 4. To determine airplane configuration at time of weighing, installed equipment is checked against the ._ airplane equipmenl list or superseding forms. All installed equipment must be in its proper place during weighing. 6-4 October 1979 BEECHCRAFT Sport lll MusketeerA23-19, 19A Section Vl Wt and Baf€quip List 5. At the time of weighing, the airplane must be level both longitudinally and laterally. Longitudinally and laterally level attitude is determined with a level on the baggage compartment floor. 6. Measurement of the reaction arms for a wheel weighing is made using a steel measuring tape. Measurements are taken, with the airplane level on the scales, from the reference (a plumb bob dropped from the centerline of airplane at F.S, 126.438, for- ward serew in spar access cover, approximately 8 to 1O inches forward of centerline drain hole) to the axle centerline of the main gear and then to the nose wheel axle centerline. The main wheel axle centerline is best located by stretching a string across from one main wheel to the other. All measurements are to be taken with the tape level with the hangar f loor and parallel to the fuselage centerline. The locations of the wheel reactions will be aBproximately at Fuselage Station 129.5 for main wheels and Fuselage Station 57.6 tor the nose wheel. 7. Jack point weighings are accomplished by placing scales at the jack points specified in step 1 above. Since the center of gravity of the airplane is forward of Fuselage Station 129"4, the tail reaction of the airplane will be in an up direction. This can be measured on regular scales by placing ballast of approximately 20O pounds on the scales to which the aft weighing point is attached by cable of adjustable length. The up reaction will then be total ballast weight minus the scale reading and is entered in the weighing form as a negative quantity. 8. Weighing should always be made in an enclosed area which is free f rom air currents. The scales used should be properly calibrated and certified" October 1 979 6-5 o o DATUM =r iig Xo riH ll E. E fo 5o Imoc) oa 9O 3E Piaa(or, 'o ro1 D= oo o I o @ @ LEVEL POINT BAGGAGE FLOOR TAIL TIE DOWN F.S. 285.9 JAC POINT F.S. 129.4 A - NOSE TO PLUMB BOB B - DATUM TO PLUMB BOB C . DATUM TO MAIN GEAR LA 7B f-c F.S. 1 .438 MODEL_SER. N \\- BASTC EMPTY WEIG!.IT ANID BALANCE REG. NO =H 6m-'r) (D; orao- D>N'l'! (, -r ,- (n .6x -J (l)= oo o E(D (o (o € o, f CL @ o FT:o ff'6' r-= Er< o) DATE JACK POINT LOCATION FORWARD 129.4 AFI' PREPARED BY Signature REACTION WHEEL - JACK PO]NTS SCALE READING TARE ITET WEIGHT ARM MOMENT LEFT MAIN RIGHT MAIN NOSE OR TAIL TOTAI- (AS WEIGHED) s P Space below provided for additions and subtractions to as weighed condition EMPTY WEIGHT (ERY} ENGINE OIL UNUSABLE FUEI. MB-l thru MB-460 Airplanes after compliance with s.l. No. 0624-28'! BASIC EMPTY WEIGHT I5.O 6.0 45.6 48.O 125.0 125.0 720 750 5700 Section Vl Wt and BalTEquip List BEECHCRAFT SPort lll MusketeerA23-19, 19A NOTE Each new airplane is delivered with a completed sample loading, basic empty weight and center of gravity, and equipment list. all pertinent to that specific airplane. lt is the owner's responsibility to ensure that changes in equipment are ref lected in a new weight and balance and in an addendum to the equipment list. There are many ways of doing this; it is suggested that a running tally of equipment changes and their effect on basic empty weight and c.g. is a suitable means for meeting both requirements. The current equipment list and empty weight and c.g. information must be retained with the airplane when it changes ownership. Beech Aircraft Corporation cannot maintain this information; the current status is known only to the owner. lf these papersbecome lost, the FAA will require that the airplane be re- weighed to establish the empty weight and c.g. and that an inventory of installed equipment be conducted to create a new equipment list. It is recommended that duplicate copies of the Basic Empty Weight and Balance sheet and the Equipment List be made and kept in an alter- nate location in the event the original hand- book is misplaced. 6-8 October 1979 \_\ WEIGHT AND BALANCE RECORD z@ ;im hmroo; qs NT! 61 -1 ta dE :J G)= oo I o J (o {(o € q, q @ o, ffiq: :o €'6' r3 o< cn (o SERTAL No. rud:eAo-- REGISTRATION NO, #zrq { PAGE NO, DATE ITEM NO. DESCRIPTION OF ARTICLE OR CHANGE WEIGHT CHANGE ADDED (+} OR REMOVED (.) RUNNING BASIC EMPTY WEIGHT IN OUT WT (rBs) ARM (tN") MOM 100 (LBs) I\4OM 100 K ile' / llrt4l b{> /*b.z/ l.{?tt7.90 +ffl , b /1 L I a,n/L4 tt ) LSU' U r"{ZA,L , >; +t.).'i <o rB ae rif,-o €' ro o o F, +Hor) oI go BiP-lJgD (oE 'o o1 D= oo o(t o @ (o SERIAL NO WEIGHT AND BALANCE HECORD REGISTBATION NO. PAGE NO. 2 DATE ITEM NO. DESCBIPTION OF ARTICLE OR CHANGE WEIGHT CHANGE ADDED (+) OB REMOVED (-) RUNNING BASIC EMPTY WEIGHT IN OUT (rBS) ARM (tN.l MOM 100 (LBS) MOM 100 BEECHCRAFT Sport lll Musketeer A23- 1 9, 1 9A Section Vl Wt and Baffiquip List WEIGHT AND BALANCE RESPONSIBILITIES The Basic Empty Weight and Moment of the airplane at the time of delivery are shown on the airplane Basic Empty Weight and Balance form. Useful load items which may be loaded into the airplane are shown on the Useful Load 1_ Weights and Moments tables" The minimum and maxi- mum moments are shown on the Moment Limits vs Weight table and can also be plotted on the Moment Limits vs Weight graph as visual indication that the limit is within the operational envelope" These moments correspond to \ the forward and aft center-of-gravity flight limits for a - panicular weight. The airplane must be loaded in such a manner to keep the center-of -gravity within these limits" October 1 979 5-11 {BS f-J Sx l\S.*\23 00 3A 3[:o' ri;-o ;' f 9 Fo IHoO oI go ;Tl!;?+ra(o1, 'o oaD= o n o o o €m 6) I { o 3 m z { tr a o)+ J N EX -.: )to Nq @n ,2(o:) <o fH o- of OU o-og f> o? ;_?AA Tff-f; Nn (Ji ooa olI] -.o fU 6l o6 9oos tt(o\ (o {(o r)AI)t,:t) AIll(:l,lAll'l' Nl()Ml,:N'l'/'10,' 24 25 26 27 28 1? l7 l0 :13. I 4 BEECHCRAFT SPort ltl Musketeer A23- 1 9, 1 9A GROSS WEIGHT MOMENT LIMITS INORMAL CATEGORY) The above weight and moment limits are based on the following weight and center of gravity limit data: Seetion Vl Wt and BafEquiP List AFT CG LIMIT r 18.3 NORMAL CATEGORY WEIGHT CONDITION 2250 lb" (max. take-o{f or I andi ng) Models: 19A, A23-19 when Beechcraft Kit 23-5003 is installed. 2200 Ib. (max. take-off or I andi ng) Model: A23-19 1800 lb. or less FWD CG LIMIT I I t.3 112.O 118.3 Min Mom. -T06- Max. Mom. -i06- Max. Mom. -116- Gross Wt Gross Wt Min. Mg-m. 100 Min, Mom. -i oo Max. Mom. -16o Gross Wt 2390 2401 24 tJ 2425 2437 2449 2461 2472 2484 2496 2508 2520 )R?') 2543 2555 2567 2579 2591 2603 2614 2626 2638 2650 2662 2020 2030 2040 2050 2060 2010 2080 2090 2100 2110 2124 ,1 ?n 2140 21 60 2170 21 80 2190 2200 2210 2220 2230 2240 ,")tri 2150 2224 2237 2250 2263 2276 2289 2303 2316 c ?ao 2342 2355 2369 2381 2395 2409 2423 2436 2450 2463 2477 2490 2504 2517 z5J I 1 897 1 908 1919 1 930 1 940 1 953 1 966 1 978 1 991 2004 201 6 2029 2042 2054 2067 2080 2092 2106 2118 2133 2144 2151 2172 21 85 2198 2211 2082 2094 2106 21 18 2129 2141 2153 21 65 2177 2189 2200 2212 2224 2236 2248 2260 227 1 2283 ,aotr 2307 2319 2331 ,'14) 2354 2366 2378 1775 1 786 1 798 181 0 1822 1 834 1 845 1 857 1 869 1 881 1 893 1 905 191 6 1928 1 940 1952 1 964 1 976 1987 1 999 201 1 2023 2035 2047 2058 2070 1 760 1770 1 780 1 790 1 800 1810 1820 1 830 1 840 1 850 1 860 1 870 1880 1 890 1 900 191 0 1 920 1 930 1 940 1 950 1 960 1970 1 980 1 990 2000 201 0 1 500 1510 1520 1 530 1 540 1 550 1 560 1 570 a tran 1 590 1 600 1610 1620 '1630 1 640 1 650 1 660 1 670 1 680 1 690 1 700 1710 1720 1730 17 40 1 750 1 617 1628 1 639 1 649 1 660 1 571 1 682 1692 1 703 17 14 1725 1 736 17 46 1757 1 768 1779 1 789 1 800 181 1 1822 1 833 1 843 1 854 1 865 1 876 1 887 October 1 979 1 07.8 118.3 6-13 Section V Perf ormance UTILITY CAT€GORY & ACROBATIC CATEGORY WEIGHT CONDITION FWD CG LIMIT 2030 ibs (max {akc oil o. 3:d,no) 1 I 0.2 tg00 ibs or tess 107.8 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A AFT CG LIMIT I 14.O t t,i.o GROSS WEIGHT MOMENT LIMTTS (UTILITY CATEGORY) {ACROBATTC CATEGOBY - 19A) The above weight and moment limits are based on the following weight and center of gravity limit data: Gross WT Min. Mom. 1T6- Max. Mom- -m6- G ross Wr Min. Mom. -T66- Max. Mom. 100 Gross wt Min. Mom. 100 Max. Mom. -]EE- 1500 1510 1 520 1 530 '1540 1550 1 560 1 570 1 580 1590 1 600 't 610 1620 1 630 1640 '1650 1 660 1 670 1 617 1628 1 639 1 649 1 660 167 1 1682 1692 1 703 17 14 1725 1 736 17 46 1757 1 768 1779 1 789 1800 1710 1721 1 733 17 44 1 756 1767 1778 1 790 1801 1813 1A24 1835 't847 1858 1870 1881 1892 1904 1 680 1 690 1 700 1710 1720 1 730 17 40 1 750 1 760 1770 1 780 1 790 1 800 1810 1820 1830 1840 1850 1811 1822 1833 1 843 1854 1865 i 876 1 887 1897 1908 1919 1 930 1940 1953 1966 1978 1991 2004 '191 5 1927 1 938 1949 1 961 19'12 't 984 1 995 2006 2018 2029 2041 2052 2063 2075 2086 2098 2109 1860 1 870 1880 1890 1900 1910 1920 1930 't940 1950 1960 1970 1980 1990 2000 2010 2020 20fi 2017 2029 2042 2055 2068 2081 2094 2107 2120 2'.t33 2145 2158 2172 2185 21 98 221 1 2224 2237 2120 2132 21 43 2155 2166 2177 2189 2200 2212 IZZJ 2234 2246 2257 2269 2280 2291 2303 2314 6-14 October 1979 BEECHCBAFTSpoTt lll MusketeerA23-19, 19A Section Vl Wt and BalTEquip List COMPI.'TING PROCEDURE Record the Basic Empty Weight and Moment f rom the Basic Empty Weight and Balance form (or from the latest superseding form) under the Basic Empty Condition block" The moment must be divided by 1OO to correspond to Useful Load Weights and Moments tables. 2. Record the weight and corresponding moment from the appropriate table of each of the useful load items (except fuel) to be carried in the airplane. 3. Total the weight column and moment column. The SUB-TOTAL is the {ero Fuel Condition. 4. Determine the weight and corresponding moment for the fuel loading to be used. This fuel loading includes fuel for the flight, plus that required for start. taxi, and take-off. Add the Fuel to Zero Fuel Condition to obtain the suB-ToTAL Ramp Condition. 5. Subtract the fuel to be used for start" taxi" and take-off to arrive at the SUB-TOTAL Take-off Condition. 6. Subtract the weight and moment of the fuel in the incremental sequence in which it is to be used from the take-off weight and rnoment" The Zero Fuel Condi- tion, the Take-Off Condition, and the Landing Condi- tion moment must be within the minimum and maxi- mum moments shown on the Moment Limit vs Weight graph for that weight. lf the total moment is less than the minimum moment allowed, useful load items must be shifted aftorforward load items reduced" lf thetotal moment is greater than the maximum moment al- lowed, useful load items must be shifted forward or aft load items reduced. lf the quantity or location of load items is changed, the calculations must be revised and the moments rechecked. October 1979 6-15 Section Vl Wt and BalTEquiP List BEECHCRAFT SPort lll Musketeer A23- 1 9, 1 9A ' The following Sample Loading chart is presented to depict ti sample meth;d of computing a load. Weights used DO NOT ref le "*- an actual airplane loading. WEIGHT AND BALANCE LOADING FORM MOD DATE - SERIAL NO. MB-XXX EG NO NXXX MOM/Ioo ITEM WEIGHT 1, BASIC EMPTY CONDITION 1437 2. FRONT SEAT OCCUPANTS 340 374 3. 3rd & 4th SEAT OCCUPANTS 140 199 4. BAGGAGE OR CARGO 45 5. SUB TOTAL ZERO FUEL CONDITION 1 962 6. FUEL LoADING (32 192 7. SUB TOTAL RAMP CO 2154 8. *LESS FUEL FO o TAXI, AND TAKE.OFF -5 64 2231 225 2456 9. SUB TOTAL TAKE-OFF CONDITION 2149 10. LESS FUEL TO DESTINATION (25 GAL) -1 50 -17 6 11. LANDING CONDITION 1 999 1 594 -6 2450 2284 *Fuel for start, taxi and take-off is normally 5 lbs at an averagc mom/100 of 6. 6-16 October 1979 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A Section Vl Wt and Baffiquip List WEIGHT AND BALANCE LOADING FORM MoDEL DATE- SERIAL NO. REG NO. NXXX "Fuel for start, taxi and take-off is normally 5 lbs at an average mom/1OO of 6. ITEM WEIGHT MOM^OO 1. BASIC EMPTY CONDITION 2. FBONT SEAT OCCUPANTS 3. 3rd & 4th SEAT OCCUPANTS 4. BAGGAGE OR CARGO 5. SUB TOTAL ZERO FUEL CONDITION 6. FUEL LOADING ( GAL) 7. SUB TOTAL RAMP CONDITION 8, *LESS FUEL FOR START, TAXI, AND TAKE.OFF 9. SUB TOTAL TAKE.OFF CONDITION 1O. LESS FUEL TO DESTINATION ( GAL) 11. LANDING CONDITION October 1979 6-17 Section Vl Wt and BalTEquip List BEECHCRAFTSpoTt lll MusketeerA23-19, 19A USEFUL LOAD WEIGHTS AND MOMENTS OCCUPANTS WEIGHT *FRONT SEATS 3RD AND 4TH SEATS BENCH SEAT ARM **110 ARM ,*142 MOM 100 MOM 100 120 130 140 150 160 170 180 190 200 132 143 154 165 176 187 198 209 220 170 185 199 213 227 24'.| 256 274 284 *Reclining seat with back in full-up position. ""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. 6-18 October 1 979 BEECHCRAFTSpoTt lll MusketeerA23-19, 19A Section Vl Wtand Baffiquip List IJSEFUL LOAD WEIGHTS ATND NIOI\fiENTS olL (lncluded in Basic Empty Weight) ARM 48 OUARTS WEIGHT MOMENT/1OO I 15 7 USABLE FUEL 5 10 15 20 22 25 30 32 35 40 45 50 52 55 5t- 58 27 37 October 1979 ABM 117 GALLONS WEIGHT MOMENT/1OO 30 60 90 120 132 150 162 180 192 210 222 240 270 300 312 330 342 348 35 70 105 140 154 176 189 211 225 246 259 281 316 351 Jb5 386 400 407 6-19 Section Vl Wtand BalTEquip List BEECHCRAFT Sport lll MusketeerA23-19, 19A USEFUL LO