SECTION I GENERAL TABLE OF CONTENTS

Raytlleon Aircraft Beech Super King Air B200 & B200C SECTION I GENERAL TABLE OF CONTENTS SUBJECT PAGE Important Notice 1-3 Use Of The Handbook................................................................ 1-3 Warnings, Cautions, And Notes 1-3 Revising The Handbook.............................................................. 1-3 Revision Service................................................................... 1-4 Airplane Flight Manual Supplements Revision Record..................................... 1-4 Supplier-Issued STC Supplements 1-4A B200 Three View..................................................................... 1-5 B200C Three View................................................................... 1-6 Ground Turning Clearance 1-7 Descriptive Data..................................................................... 1-8 Engines.......................................................................... 1-8 Number of Engines............................................................... 1-8 Engine Manufacturer............................................................. 1-8 Engine Model Number............................................................ 1-8 Engine Type 0 1-8 Number of Drive Shafts 1-8 Compressor Stages and Types 1-8 Combustion Chamber Type........................................................ 1-8 Turbine Stages and Types 0 1-8 Compressor (Gas Generator) Turbine 1-8 Power Turbine................................................................ 1-8 Engine Shaft-Horsepower Rating.................................................... 1-8 Compressor (Gas Generator) Shaft Rotational Speed (N 1 ) Limits 1-8 Propeller Rotational Speed (N 2 ) Limits 1-8 Propellers........................................................................ 1-8 Number of Propellers............................................................. 1-8 Propeller Manufacturer............................................................ 1-9 Number of Blades................................................................ 1-9 Propeller Diameter............................................................... 1-9 Propeller Type 1-9 Pitch Range (30-inch Station) 1-9 Fuel 1-9 Approved Engine Fuels........................................................... 1-9 Commercial Grades............................................................ 1-9 Military Grades 1-9 Emergency Fuels................................................................ 1-9 Commercial Aviation Gasoline Grades 1-9 Military Aviation Gasoline Grades 1-9. Usable Fuel.................................................. 1-9 Approved Fuel Additives 1-9 Engine Oil 1-10 Specification................................................................... 1-10 Oil Capacity (Each Engine) 1-10 Maximum Certificated Weights....................................................... 1-10 Cabin and Entry Dimensions......................................................... 1-10 Specific Loadings................................................................. 1-10 May, 2000 1-1

Beech Super King Air B200 & B200C Raytlleon Aircraft SECTION I GENERAL TABLE OF CONTENTS (CONT'D) SUBJECT PAGE Symbols, Abbreviations, and Terminology 1-11 Airspeed Terminology 1-11 Meteorological Terminology 1-12 Power Terminology 1-12 Control and Instrument Terminology 1-13 Graph and Tabular Terminology 1-13 Weight and Balance Terminology 1-14 1-2 May, 2000

Raytbeon Aircraft IMPORTANT NOTICE Beech Super King Air 8200 & B200C Section I - This handbook should be read carefully by the owner and the operator in order to become familiar with the operation of the airplane. Suggestions and recommendations have been made within it to aid in obtaining maximum performance without sacrificing economy. Be familiar with, and operate the airplane in accordance with, the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual and/or placards which are located in the airplane. As a further reminder, the owner and the operatorshould also be familiar with the Federal Aviation Regulations applicable to the operation and maintenance of the airplane, and FAR Part 91, Operating and Flight Rules. Further, the airplane must be operated and maintained in accordancewith FAA Airworthiness Directives which may be issued against it. The Federal Aviation Regulations place the responsibility for the maintenance of this airplane on the owner and the operator, who should ensure that all maintenance is done by qualified mechanics in conformity with all airworthiness requirements established for this airplane. All limits, procedures, safety practices, time limits, servicing, and maintenance requirements contained in this handbook are considered mandatory for continued airworthiness and to maintain the airplane in a condition equal to that of its original manufacture. Raytheon Aircraft Authorized Outlets can provide recommended modification, service, and operating procedures issued by both the FAA and Raytheon Aircraft Company, which are designed to get maximum utility and safety from the airplane. I USE OF THE HANDBOOK WARNINGS, CAUTIONS, AND NOTES The following definitions apply to (WARNINGS), (CAUTIONS), and (NOTES) found throughout the handbook: IWARNING I Operating procedures, techniques, etc., which could result in personal injury or loss of life if not carefully followed. Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed. NOTE An operating procedure, technique, etc., which is considered essential to emphasize. REVISING THE HANDBOOK The Pilot's Operating Handbook is designedto facilitate maintaining the documents necessaryfor the safe and efficient operation of the airplane. The handbook has been prepared in loose leaf form for ease in maintenance. It incorporates quick-reference tabs imprinted with the title of each section. NOTE In an effort to provide as complete coverage as possible, applicable to any configuration of the airplane, some optional equipment has been included in the scope of the handbook. However, due to the variety of airplane appointments and arrangements available, optional equipment described or depicted herein may not be designated as such in every case. May, 2000 1-3

Beech Super King Air 8200 & 8200C Section I -.avllleor Aircraft Immediately following the Title Page is a List Of Effective Pages. A complete listing of all pages is presented along with the current status of the material contained; Le. Original, Reissued or Revised. Also, in the lower right corner of the blocked portion is a box containing a capital letter which denotes reissue of the manual. It will be advanced one letter, alphabetically, per reissue. A reissue of the manual or the revision of any portion will be received with a new List Of Effective Pages to replace the previous one. Reference to the List Of Effective Page(s) enables the user to determine the current issue, revision, or reissue in effect for each page in the handbook, (except for the Supplements Section). I When the handbook is originally issued, and each time it is revised or reissued, a new Log Of Revisions page is provided, immediately following the List Of Effective Pages. All Log Of Revisions pages must be retained until the handbook is reissued. A capital letter in the lower right cornerof the Log Of Revisions page designates the Original Issue ("A") or reissue ("BII, "C", etc.) covered by the Log page. If a number follows the letter, it designates the sequential revision (1st, 2nd, 3rd, etc.,) to the Original Issue or reissue covered by the Log Of Revisions page. Reference to the Log Of Revisions page(s) enables the user to determine the current issue, revision, or reissue in effect for each page in the handbook (except for the Supplements Section), and provides a record of changes made since the Original Issue or the latest reissue. That portion of the text or an illustration which has been revised by the addition of, or a change in, information is denoted by a solid revision bar located adjacent to the area of change and placed along the outside margin of a page. REVISION SERVICE The following publications will be provided, at no charge, to the registered owner/operator of this airplane: 1. Reissues and revisions of Pilot's Operating Manual and FAA Approved Airplane Flight Manual. 2. Original issues and revisions of FAA Approved Airplane Flight Manual Supplements. 3. Original issues and revisions of Raytheon Aircraft Service Bulletins. The above publications will be provided to the registered owner/operator at the address listed on the FAA Aircraft Registration Branch List or the Raytheon Aircraft Domesticllnternational Owners Notification List. Further, the owner/operator will receive only those publications pertaining to the registered airplane serial number. For detailed information on how to obtain "Revision Service ll applicable to this manual or other Raytheon Aircraft Service Publications, consult any Raytheon Aircraft authorized outlet, or refer to the latest revision of Raytheon Aircraft Service Bulletin No. 2001. Raytheon AircraftCorporation expressly reservesthe right to supersede, cancel, and/or declare obsolete, without prior notice, any part, part number, kit, or publication referenced in this manual. The owner/operator should always refer to all supplements, whether STC Supplements or Raytheon Aircraft Supplements, for possible placards, limitations, emergency, abnormal, normal, and other operational procedures for proper operation of the airplane with optional equipment installed. IWARNING I It shall be the responsibility of the owner/operator to ensure that the latest revisions of publications referenced in this manual are utilized during operation, servicing, and maintenance of the airplane. AIRPLANE FLIGHT MANUAL SUPPLEMENTS REVISION RECORD Section IX contains the FAA Approved Airplane Flight Manual Supplements headed by a Log of Supplements page. On the Log page is a listing of the FAA Approved Supplemental Equipment available for installation on the airplane. When new supplements are received or existing supplements are revised, a new Log page will replace the previous one, since it contains a listing of all previous approvals, plus the new approval. The supplemental material will be added to the Section in accordance with the sequence specified on the Log page. 1-4 May, 2000

Raytlleon Aircraft Beech Super King Air 8200 & B200C Section I - NOTE Upon receipt of a new or revised supplement, compare the existing Log of Supplements in the handbook with the corresponding applicable Log page accompanying the new or revised supplement. It may occur that the Log page already in the handbook is dated later than the Log page accompanying the new or revised supplement. In any case, retain the Log page having the later date in the folio at the bottom-left corner of the page, and discard the older Log page. SUPPLIER-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 Raytheon Aircraft Flight Manual Supplement for every installed item requiring a supplement. If a new handbook for operation of the airplane is obtained at a later date, it is the responsibility 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. May, 2000 1-4A

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~ft Super King Air B2001B200C Section I ;...- 43' 10" (1) -, 43' 9" (2) 14' 10" (1) 14' 6" (2) 14.5"(1).(3)~114 11.5" (1) 14.04" (2), (3) I 14' 11.4" (2) 14.75" (1), (4) 14.29" (2), (4) _t. CONFIGURATIONS: (1) STANDARD LANDING GEAR (2) HIGH FLOTATION LANDING GEAR (3) HARTZELL PROPELLER (4) McCAULEY PROPELLER!-e-----18' 5"---- ~------------54'6"------------- = ~. 8' 2.5" DIA (3) I 8' 2" DIA (4) I 1 8200 THREE VIEW 200-607-1 001 December, 1994 1-5

Section I ~ft Super King Air B2001B200C :--- 43' 10" (1) -, 43' 9" (2) 14' 10" (1) 14' 6" (2) 14.5" (1), (3) ;-.1_-=_114' 11.5" (1) 14.04" (2), (3) I 14' 11.4" (2)---l 14.75" (1), (4) 14.29" (2), (4) CONFIGURATIONS: (1) STANDARD LANDING GEAR (2) HIGH FLOTATION LANDING GEAR (3) HARTZELL PROPELLER (4) McCAULEY PROPELLER :------18' 5"---~ r---------------54' 6"------------.-1 8' 2.5" DIA (3) 8' 2" DIA (4) B200C THREE VIEW 200-607-8 001 1-6 December, 1994

~ft Super King Air B200/B200C Section I GROUND TURNING CLEARANCE 200 601 37 Radius for Inside Gear. Radius for Nose Wheel. Radius for Outside Gear. Radius for Wing Tip... 4 feet 19 feet 21 feet 39 feet o inches 6 inches 1 inch 10 inches TURNING RADII ARE PREDICA TED ON THE USE OF PARTIAL BRAKING ACTION AND DIFFERENTIAL POWER December, 1994 1-7

Section I ~ft Super King Air B200/B200C DESCRIPTIVE DATA ENGINES NUMBER OF ENGINES Two ENGINE MANUFACTURER Pratt & Whitney Canada (Longueuil, Quebec, Canada) ENGINE MODEL NUMBER PT6A-42 ENGINE TYPE Turbo-propeller Engine NUMBER OF DRIVE SHAFTS Two 1 Compressor (Gas Generator) Shaft 1 Power Turbine Shaft COMPRESSOR STAGES AND TYPES 3 Axial-flow Stages 1 Centrifugal-flow Stage COMBUSTION CHAMBER TYPE Annular TURBINE STAGES AND TYPES COMPRESSOR (GAS GENERATOR) TURBINE Single-stage Axial-flow Reaction Turbine POWER TURBINE Two-stage Axial-flow Reaction Turbine ENGINE SHAFT-HORSEPOWER RATING 850 SHP COMPRESSOR (GAS GENERATOR) SHAFT ROTATIONAL SPEED (Nt) LIMITS Take-off, Maximum Continuous, Cruise Climb, Maximum Cruise, Normal Cruise Power: 101.5% N1 (38,100 rpm) PROPELLER ROTATIONAL SPEED (N2) LIMITS Take-oft, Maximum Continuous, Cruise Climb, Maximum Cruise, Normal Cruise Power: 2000 rpm PROPELLERS NUMBER OF PROPELLERS Two 1-8 December, 1994

ikechcmft Super King Air B200JB200C section I PROPELLER MANUFACTURER Hartzell Propeller, Inc. (Piqua, Ohio) McCauley Propeller (Vandalia, Ohio) NUMBER OF BLADES Three PROPELLER DIAMETER Hartzell Propeller - 98.5 inches McCauley Propeller - 98.0 inches PROPELLER TYPE Constant-speed, FuJi-feathering, Reversing, Counter-weighted, Hydraulically Actuated PITCH RANGE (3D-INCH STATION) Hartzell Propeller: Feathered +90, Reverse _9 McCauley Propeller: Feathered+ 86.8, Reverse -10 FUEL APPROVED ENGINE FUELS COMMERCIAL GRADES Jet A, Jet A-1, Jet B MILITARY GRADES JP-4, JP-5, JP-8 EMERGENCY ENGINE FUELS (SEE LIMITATIONS SECTION FOR LIMITATIONS) COMMERCIAL AVIATION GASOLINE GRADES 80 Red (Formerly 80/87) 91/98 100LL Blue'* 100 Green (Formerly 100/130) 115/145 Purple rtn some countries, this fuel is colored Green and designated"100l." MILITARY AVIATION GASOLINE GRADES 80/87 Red 100/130 Green 115/145 Purple USABLE FUEL Main Fuel System.........386 gallons Auxiliary Fuel System Maximum Usable Fuel Quantity 158 gallons 544 gallons APPROVED FUEL ADDITIVES Anti-ice additive conforming to Specification MIL-I-27686 or equivalent, is permissible. Use not less than 20 11 oz of additive per 260 gallons of fuel or more than 20 fl oz additive per 104 gallons of fuel. December, 1994 1-9

Section I ~ft Super King Air B200/B200C Fuel biocide "BIOBOR JF" in concentrations of 135 ppm or 270 ppm. Refer to the SuperKingAir 200 Series Maintenance Manual and Pratt & Whitney Service Bulletin No. 1244 for concentrations to use and for procedures for adding BIOBOR JF to the airplane fuel. ENGINE OIL SPECIFICATION Any oil specified by brand name in the latest revision of Pratt & Whitney Service Bulletin Number 3001. Refer to "CONSUMABLE MATERIALS" in the HANDLING, SERVICING & MAINTENANCE Section. OIL CAPACIT'I (EACH ENGINE) Total 14.2 U.S. quarts Undrainable..........1.5 U.S. quarts Refill Capacity............... 12.7 U.S. quarts Operating Range Full to 4.0 U.S. Quarts low MAXIMUM CERTIFICATED WEIGHTS I Maximum Ramp Weight.........12,590 pounds Maximum Take-offWeight 12,500 pounds Maximum L.anding Weight 12,500 pounds Maximum Zero Fuel Weight.......11,000 pounds Maximum Weight in Baggage Compartment: B8-1052, BB 1091 and after, BL 58 and after, and prior airplanes with Beech Kit #101-5068-1 installed: When Equipped with FOld-up Seats ~ 510 pounds When Not Equipped with Fold-up Seats or; Prior to BB-1091, except BB-1052, and prior to BL-58 without Beech Kit'101-5068-1 installed: When Equipped with FOld-up Seats 550 pounds 370 pounds When Not Equipped with Fold-up Seats.....410 pounds CABIN AND ENTRY DIMENSIONS Cabin Wic:ttl1 (Maximum)............54 inches Cabin Length (Maximum between pressure bulkheads)......22 feet Cabin Height (Maximum) 57 inches Airstair Entrance Door Width (Minimum) (B200)............26.75 inches Airstair Entrance Door Height (Minimum) (8200) 51.5 inches Airstair Entrance Door Width (Minimum) (B200C).........20.2 inches Airstair Entrance Door Height (Minimum) (B200C)..........46 inches Cargo Door Width (Minimum) (B200C) 49 inches Cargo Door Height (Minimum) (B200C) 52 inches Pressure Vessel Volume......393 cubic feet Potential Cargo-area Volume 253 cubic feet SPECIFIC LOADINGS WING LOADING: 41.3 pounds per square foot POWER LOADING: 7.4 pounds per shaft horsepower 1 10 April, 1996

~ft Super King Air B200/B200C Section I SYMBOLS, ABBREVIATIONS, AND TERMINOLOGY The following glossary is applicable within this handbook. GENERAL AIRSPEED TERMINOLOGY CAS GS las KCAS KIAS M TAS Vso VSSE Calibrated Airspeed is the indicated airspeed of an airplane corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. 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. las values published in this handbook assume zero instrument error. Calibrated Airspeed expressed in knots. Indicated Airspeed expressed in knots. Mach Number is the ratio of true airspeed to the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed air, which is the CAS corrected for altitude, temperature, and compressibility. Take-off Decision Speed. Take-off Safety Speed Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. Design Flap Speed is the highest speed permissible at which wing flaps may be actuated. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an airplane 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. Air Minimum Control Speed is the minimum flight speed at which the airplane is directionally controllable as determined in accordance with Federal Aviation Regulations. The airplane certification conditions include one engine becoming inoperative and windmilling, a 5-degree bank towards the operative engine, take-off power on operative engine, landing gear up, flaps in the take-off position, and most rearward C.G. For some conditions of weight and altitude, stall can be encountered at speeds above VMCA as established by the certification procedure described above, in which event stall speed must be regarded as the limit of effective directional control. Ground Minimum Control Speed Maximum Operating Limit Speed is the speed limit that may not be deliberately exceeded in normal flight operations. V is expressed in knots and M in Mach Number. Rotation Speed Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. Intentional One-Engine-Inoperative Speed is a speed above both VMCA and stall speed, selected to provide a margin of lateral and directional control when one engine is suddenly rendered inoperative. Intentional failing of one engine below this speed is not recommended. December, 1994 1-11

Section I Vx VXSE Vy VYSE ~ft Super King Air B2001B200C Best Angle-at-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance with gear and flaps up. One-Engine-Inoperative Best Angle-at-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible horizontal distance with one engine inoperative. Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time with gear and flaps up. One-Engine-Inoperative Best Rate-at-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time with one engine inoperative. METEOROLOGICAL TERMINOLOGY Altimeter Setting Indicated Pressure Altitude IOAT ISA OAT Pressure Altitude Station Pressure Temperature Compressibility Effects Wind Barometric Pressure corrected to sea level. The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). Indicated Outside Air Temperature is the temperature value read from an indicator. 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 of mercury (1013.2 millibars); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5 0 Centigrade (-69.7 Fahrenheit) is -0.00198 Centigrade (0.003566 Fahrenheit) per foot and zero above that altitude. Outside Air Temperature is the free air static temperature obtained either from the temperature indicator (IOAT) adjusted for compressibility effects, or from ground meteorological sources. Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure (barometric) altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Position errors may be obtained from the Altimeter Correction graphs. Actual atmospheric pressure at field elevation. An error in the indication of temperature caused by airflow over the temperature probe. The error varies, depending on altitude and airspeed. 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. POWER TERMINOLOGY Beta Range Cruise Climb High Idle Low Idle Maximum Continuous Power The region of the Power Lever control which is aft of the Idle Stop and forward of reversing range where blade pitch angle can be changed without a change of gas generator rpm. Is the maximum power approved for normal climb. These powers are torque or temperature {ITT} limited. Obtained by placing the Condition Lever in the High Idle Position. This limits the power operation to a minimum of 70% of N1 rpm. Obtained by placing the Condition Lever in the Low Idle position. This limits the power operation to a minimum of 56% of N1 rpm. Is the highest power rating not limited by time. Use of this rating is intended for emergency situations at the discretion of the pilot. 1-12 December, 1994

~ft Super King Air B200/B200C Section I Maximum Cruise Power Reverse SHP Take-off Power Is the highest power rating for cruise and is not time limited. Reverse thrust is obtained by lifting the Power Levers and moving them aft of the Beta range. Shaft Horsepower. Is the maximum power rating and is limited to a maximum of 5 minutes operation. use of this rating should be limited to normal take-off operations and emergency situations. CONTROL AND INSTRUMENT TERMINOLOGY Condition Lever (Fuel Shut-off Lever) ITT (Interstage Turbine Temperature) N1 Tachometer (Gas Generator RPM) Power Lever (Gas Generator N1 RPM) Propeller Control Lever (N2 RPM) Propeller Governor Torquemeter -The fuel shut-off lever actuates a valve in the fuel control unit which controls the flow of fuel at the tuel control outlet and regulates the idle range from Low to High Idle. Eight probes wired in parallel indicate the temperature between the compressor and power turbines. The tachometer registers the rpm of the gas generator with 1000/0 representing a gas generator speed of 37,500 rpm. This lever serves to modulate engine power from full reverse thrust to takeoff. The position for idle represents the lowest recommended level of power for flight operation. This lever is used to control the rpm setting of the propeller governor. Movement of the lever results in an increase or decrease in propeller rpm. Propeller feathering is the result of lever movement beyond the detents at the low rpm (high pitch) end of the lever travel. The propeller governor senses changes in rpm and hydraulically changes propeller blade angle to compensate for the changes in rpm. Constant propeller rpm is thereby maintained at the selected rpm setting. The torquemeter system indicates the shaft output torque. Differential pressure from a mechanism within the reduction gear case causes a bellows and servo system to indicate torque on a meter. Instrument readout is in foot-pounds. GRAPH AND TABULAR TERMINOLOGY Accelerate-Go Accelerate-Stop AGL Best Angle of Climb Best Rate of Climb Clearway The distance to accelerate to Take-off Decision Speed (V1), experience an engine failure, continue accelerating to lift-off, then climb and accelerate in order to achieve Take-off Safety Speed (V2) at 35 feet above the runway. The distance to accelerate to Take-off Decision Speed (V1) and bring the airplane to a stop. Above Ground Level The best angle-at-climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance with gear and flaps up. The best rate-ot-climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible time with gear and flaps up. A clearway is an area beyond the airport runway not less than 500 feet wide, centrally located about the extended centerline of the runway, and under the control of the airport authorities. The clearway is expessed in terms of a clear plane, extending from the end of the runway with an upward slope not exceeding 1.25 percent, above which no object nor any terrain protrudes. However, threshold lights may protrude above the plane if their height above the end of the runway is 26 inches or less and if they are located to each side of the runway. December, 1994 1-13

Section I ~ft Super King Air 8200/B200C Climb Gradient Demonstrated Crosswind MEA Net Gradient of Climb Route Segment Take-off Flight Path The ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. The maximum go-degree crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification. The value shown is not limiting. Minimum Enroute Altitude The gradient of climb with the flaps in the take-off position, and the landing gear retracted. "Net" indicates that the actual gradients of climb have been reduced by.8% to allow for turbulence and pilot technique. The Net Gradient of Climb graphs are constructed so that the value(s) obtained using the airport pressure altitude and outside air temperature will be the average gradient from 35 ft above the runway up to 1500 ft above the runway. A part of a route. Each end of that part is identified by: (1) a geographic location; or (2) a point at which a definite radio fix can be established. The minimum gradient of climb required to clear obstacles in excess of 35 feet, measured horizontally from reference zero and vertically at the altitude above the runway. Reference zero is the point where the airplane has reached 35 feet above the runway as determined from the Accelerate-Go graphs. WEIGHT AND BALANCE TERMINOLOGY Approved Loading Envelope Arm Basic Empty Weight Center of Gravity CG Limits Datum Empty Weight Engine Oil Jack Point Landing Weight Leveling Points Maximum Weight Moment Those combinations of airplane weight and center of gravity which define the limits beyond which, loading is not approved. The distance from the center of gravity of an object to a line about which moments are to be computed. The weight of an empty airplane including full engine oil and unusable fuel. This equals empty weight plus the weight of unusable fuel, and the weight of all the engine oil required to fill the lines and tanks. Basic empty weight is the basic configuration from which loading data is determined. A point at which the weight of an object may be considered concentrated for weight and balance purposes. The extreme center of gravity locations within which the airplane must be operated at a given weight. A vertical plane perpendicular to the airplane longitudinal axis from which fore and aft (usually aft) measurements are made for weight and balance purposes. The weight of an empty airplane before any oil or fuel has been added. This includes all permanently installed equipment, fixed ballast, full hydraulic fluid, full chemical toilet fluid, and all other operating fluids full, except that the engines, tanks, and lines do not contain any engine oil or fuel. That portion of the engine oil which can be drained from the engine. Points on the airplane identified by the manufacturer as suitable for supporting the airplane for weighing or other purposes. The weight of the airplane at landing touchdown. Those points which are used during the weighing process to level the airplane. The largest weight allowed by design, structural, performance or other limitations. A measure of the rotational tendency of a weight, about a specified line, mathematically equal to the product of the weight and the arm. 1-14 December, 1994

~ft Super King Air B200/B200C Section I Payload Ramp Weight Station Take-off Weight Tare Unusable Fuel Usable Fuel Useful Load Zero Fuel Weight Weight of occupants, cargo and baggage. The airplane weight at engine start assuming all loading is completed. The longitudinal distance from some 'point to the zero datum or zero fuselage station. The weight of the airplane at lift-off from the runway. The weight which may be indicated by a set of scales before any load is applied. The fuel remaining after consumption of usable fuel. That portion of the total fuel which is available for consumption as determined in accordance with applicable regulatory standards. The difference between the airplane ramp weight and the basic empty weight. The airplane ramp weight minus the weight of usable fuel on board. December, 1994 1-15

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