Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

BEECHCRAFT Duchess 76 are considered mandatory for continued airworthiness to maintain the airplane in a condition equal to that of its original manufacture. Authorized BEECHCRAFT Aero or Aviation Centers or International Distributors or Dealers can provide recommended modification, service, and operating procedures issued by both the FAA and Beech Aircraft Corporation, which are designed to get maximum utility and safety from the airplane. USE OF THE HANDBOOK The Pilot's Operating Handbook is designed to facilitate maintaining the documents necessary for the safe and effi- cient 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 ar- ranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions. I / } 1-4 Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 Section 9 Section 10 General Limitations Emergency Procedures Normal Procedures Performance Weight and Balance/Equipment List Systems Description Handling, Servicing, and Maintenance Supplements Safety Information August, 1980 BEECHCRAFT Duchess 76 NOTE Section I General The owner/operator should always refer to all supplements, whether STC Supplements or Beech Supplements, for possible placards, limitations, normal, emergency and other operational procedures for proper operation of the airplane with optional equipment installed. The following information may be provided to the holder of this manual automatically: 1. Original issues and revisions of Class I and Class II Service Instructions 2. Original issues and revisions of FAA Approved Airplane Flight Manual Supplements 3. Reissues and revisions of FAA Approved Airplane Flight Manuals, Flight Handbooks, Owner's Manuals, Pilot's Operating Manuals, and Pilot's Operating Handbooks This service is free and will be provided only to airplane owners who are listed on the FAA Aircraft Registration Branch List or the BEECHCRAFT International Owners Notification Service List, and then only if listed by airplane serial number for the model for which this handbook is applicable. For detailed information on how to obtain "Revision Service" applicable to this handbook or other BEECHCRAFT Service Publications consult any BEECHCRAFT Aero or Aviation Center, International Distributor, or International Dealer, or refer to the latest revision of BEECHCRAFT Service Instructions No. 0250-010. September, 1983 1-5 Section I General BEECH CRAFT Duchess 76 Due to the large variety of airplane configura- tions available through optional equipment, it should be noted that where information pertain- ing to optional equipment appears in the hand- book, the optional equipment will not normally be designated as such. Due to custom design varia- tions, the illustrations in this handbook will not be typical of every airplane. Beech Aircraft Corporation expressly reserves the right to supersede, cancel, and/or declare obsolete, without prior notice, any part, part number, kit, or publication that may be refer- enced in this handbook. REVISING THE HANDBOOK Immediately following the Title Page is the "Log of Revi- sions" page(s). The Log of Revisions pages are used for maintaining a listing of all effective pages in the handbook (except the SUPPLEMENTS section), and as a record of revisions to these pages. In the lower right corner of the outlined portion is a box containing a capital letter which denotes the issue or reissue of the handbook. It will be advanced one letter, alphabetically, per reissue. This letter will be suffixed by a number whenever the handbook is revised. When a revision to the handbook is made, a new Log of Revisions will be issued. All Logs of Revisions must be retained in the handbook to pro,vide a complete record of material status until a reissue is made. ,) 1-6 September, 1983 BEECHCRAFT Duchess 76 WARNING Section I General When this handbook is used for airplane opera- tional purposes it is the pilot's responsibility to maintain it in current status. AIRPLANE FLIGHT MANUAL SUPPLEMENTS REVISION RECORD Section IX contains the FAA Approved Airplane Flight Man- ual Supplements headed by a Log of Supplements page. On the "Log" page is a listing of the FAA Approved Supplemen- tal 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 grouping in accordance with the descriptive listing. NOTE 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 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. 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. September, 1983 1·6A ( >lNV1S ~31 A1'VNOI.LN31.NI 9LssC»4:>no .L:IVI:JOH033S BEECHCRAFT Duchess 76 section I General o o o o r ._------, WING AREA: 181 SQ. FT. I ,,I .--------, ~12:6"-J 76" DIA. = ~ => 76-607·4 OJ I 38' 29'5" Ci=--- ~TI I I 9'6" THREE-VIEW January 1978 1-7 Section I General BEECHCRAFT Duchess 76 ® 76-604·2 GROUND TURNING CLEARANCE ® Radius for Wing Tip 27 feet 2 inches @ Radius for Nose Wheel 9 feet 10 inches © Radius for Inside Gear 3 feet 1 inch @ Radius for Outside Gear 13 feet 8 inches TURNING RADII ARE PREDICATED ON THE USE OF PARTIAL BRAKING ACTION AND DIFFERENTIAL POWER. ) 1-8 January 1978 BEECHCRAFT Duchess 76 DESCRIPTIVE DATA ENGINES section I General Two Avco Lycoming engines are installed; one 0-360- A1 G6D (clockwise rotating) located on the left wing, and one LO-360-A1G6D (counterclockwise rotating) located on the right wing. The engines are four-cylinder, direct-drive. hori- zontally opposed, and each rated at 180 horsepower at 2700 rpm. Take-off and Maximum Continuous Power . . . . . Full throttle, 2700 rpm Recommended Maximum Cruise Power. . . . . . . . . . . 24 in. Hg, 2700 rpm PROPELLERS The airplane is equipped with two Hartzell, constant-speed, full-feathering, two-blade propellers: the left engine (clock- wise rotating) has an HC-M2YR-2CEUF hub with FC 7666A blades and a C2285-3P spinner; the right engine (coun- terclockwise rotating) incorporates an HC-M2YR-2CLEUF hub with FJC 7666A blades and a C2285-3LP spinner. Pitch settings at the 30 inch station: Low, 12.1° :!: .1°; High, 1r to 20°; Feathered, 81° + 1°, Diameter is 76 inches, with cut-off permitted to 74.0 inches. January 1978 1-9 Section I General FUEL BEECHCRAFT Duchess 76 Aviation Gasoline, grade 100 (green) or grade 100 LL (blue). Total Capacity Total Usable . OIL 103 gallons 100 gallons I Engine oils must meet Avco Lycoming Specification No. I 301 F and be used in accordance with Avco Lycoming Service Instructions No. 1014J or subsequent revisions. Refer to HANDLING, SERVICING, AND MAINTENANCE section for a list of oils meeting this specification. Average Ambient MIL-L-6082 MIL-L-22851 Air Temperature Grades Ashless Dispersant Grades Above 60 F SAE 50 SAE 40 or SAE 50 300 to 90°F SAE 40 SAE 40 o 0 SAE 30 SAE 40, SAE 30 o to 70 F or SAE 20W40 0 SAE 20 SAE 30 or SAE 20W30 Below 10 F Oil Capacity 8 quarts each engine MAXIMUM CERTIFICATED WEIGHTS ) MaximumHamp Weight . Maximum Take-off Weight Maximum Landing Weight Maximum Zero Fuel Weight Maximum Weight in Baggage Compartment 39161bs 3900lbs 3900lbs 3500lbs . 200lbs 1-10 September, 1983 BEECHCRAFT Duchess 76 STANDARD AIRPLANE WEIGHTS Standard Empty Weight Maximum Useful Load . CABIN AND ENTRY DIMENSIONS Cabin Width (maximum) . Cabin Length (maximum) Cabin Height (maximum) . Cabin Door .. Door Sill Height . . . . . Section I General 24461bs 1470lbs .3ft8in. 7 ft 11 in. . . . 4 ft 36 in. x 38 in. . . . . 2in. BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Volume . . . . Compartment Width (nominal) Compartment Length (nominal) Compartment Height (nominal) Door Width (minimum) . Door Height (minimum) . . . SPECIFIC LOADINGS 19.5 cu ft 38 in. 26in. 37in. 22in. 33in. Wing Loading at Maximum Take-off Weight. . 21.5Ibs/sq ft Power Loading at Maximum Take-off Weight 10.8Ibs/hp 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. January 1978 1-11 section I General BEECHCRAFT Duchess 76 AIRSPEED TERMINOLOGY lAS Indicated Airspeed is the speed of an airplane as shown on its airspeed indi- cator. As used within this handbook lAS assumes no instrument error. CAS TAS GS YMCA 1-12 Calibrated Airspeed is the indicated air- speed of an airplane, corrected for posi- tion and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. True Airspeed is the airspeed of an air- plane relative to undisturbed air which is the CAS corrected for altitude, tem- perature, and compressibility. Ground Speed is the speed of an air- plane relative to the ground. Air Minimum Control Speed is the minimum flight speed at which the air- plane is directionally controllable as de- termined in accordance with Federal Aviation Regulations. The airplane cer- tification conditions include one engine becoming inoperative and windmilling, a 5-degree bank towards the operative engine, take-off power on operative en- gine, landing gear up, flaps in take-off position, and most rearward C.G. For some conditions of weight and altitude, stall can be encountered at speeds above YMCA as established by the cer- tification procedure described above, in which event stall speed must be re- garded as the limit of effective direc- tional control. January 1978 ) BEECHCRAFT Duchess 76 VSSE VA VF VFE VLE VLO VNE April 1979 Section I General The Intentional One-Engine- Inoperative Speed is a speed above both VMCA and stall speed, selected to provide a margin of lateral and direc- tional control when one engine is sud- denly rendered inoperative. Intentional failing of one engine below this speed is not recommended. I Maneuvering Speed is the maximum speed at which application of full avail- able aerodynamic control will not over- stress 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 ex- tended or retracted. Never Exceed Speed is the speed limit that may not be exceeded at any time. 1-13 Section I General VNO Vs VSO Vx Vy BeECHCRAFT Duchess 76 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum 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 configura- tion. Best Angle-of-Climb Speed is the air- speed which delivers the greatest gain of altitude in the shortest possible hori- zontal distance. Best Rate-Of-Climb Speed is the air- speed which delivers the greatest gain in altitude in the shortest possible time. METEOROLOGICAL TERMINOLOGY ISA 1-14 International Standard Atmosphere in which: (1) The air is a dry pertect gas; (2) The temperature at sea level is 15° Celsius (59° Fahrenheit); (3) The pressure at sea level is 29.92 in. Hg (1013.2 millibars); (4) The temperature gradient from sea level to the altitude at which the temperature is - 56.5°C (-69.rF) is -0.00198°C (- 0.003566°F) per foot and zero above that altitude. January 1978 BEECHCRAFT Duchess 76 OAT Indicated Pressure Altitude Pressure Altitude Station Pressure Wind Section I General Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indications ad- justed for instrument error and com- pressibility effects, or ground meteorological sources. The number actually read from an altimeter when the barometri c subscale has been set tc 29.92 in. Hg (1013.2 millibars). I Altitude measured from standard 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. In this handbook, altimeter instrument errors are assumed to be zero. Position errors may be obtained Ifrom the Altimeter Correction graph. Actual atmospheric pressure at field elevation. The wind velocities recorded as vari- ables on the charts of this handbook are to be understood as the headwind or tailwind components of the reported winds. POWER TERMINOLOGY Take-off and Maximum Continuous Cruise Climb April 1979 Highest power rating not limited by time. Power recommended for cruise climb. 1-15 Section I General ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY BEECHCRAFT Duchess 76 Throttle Control Propeller Control Mixture Control Tachometer Propeller Governor Manifold Pressure EGT 1-16 The lever used to control power by in- troducing fuel-air mixture into the intake passages of the engine. Settings are reflected by readings on the manifold pressure gage. This lever requests the governor to maintain rpm at a selected value and, in the maximum decrease rpm position, feathers the propeller. This lever is used to set fuel flow in all modes of operation and cuts off fuel completely for engine shutdown. Indicates the rotational speed of the en- gine/propeller in revolutions per minute (rpm). Regulates the rpm of the engine/propel- ler by increasing or decreasing the pro- peller pitch through a pitch change mechanism in the propeller hub. An instrument that measures the abso- lute pressure in the intake manifold of an engine, expressed in inches of mer- cury (in. Hg). The Exhaust Gas Temperature Indi- cator is used to identify the lean and best-power fuel flow mixtures for vari- ous power settings during cruise. January 1978 I BEECHCRAFT Duchess 76 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY section I General Climb Gradient Demonstrated Crosswind Velocity Accelerate- Stop Distance Accelerate- Go Distance MEA Route Segment September, 1983 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 velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The value I shown is not limiting. The distance required to accelerate an airplane to a specified speed and, as- suming failure of an engine at the in- stant that speed is attained, to bring the airplane to a stop. The distance required to accelerate an airplane to a specified speed and, as- suming failure of an engine at the in- stant that speed is attained, feather in- operative propeller and continue takeoff on the remaining engine to a height of 50 feet. Minimum Enroute IFR Altitude. A part of a route. Each end of that part is identified by: (1 ) A geographical location: or (2) A point at which a definite radio fix can be established 1-17 Section I General WEIGHT AND BALANCE TERMINOLOGY BEECHCRAFT Duchess 76 Standard Empty Weight Basic Empty Weight Usable Fuel Unusable Fuel Payload Useful Load Maximum Ramp Weight Maximum Take-Off Weight Maximum Landing Weight Maximum Zero Fuel Weight 1-18 Weight of a standard airplane including unusable fuel, full operating fluids, and fu II oil. Standard empty weight plus optional equipment. Fuel available for flight planning. Fuel remaining after a runout test has been completed in accordance with governmental regulations. Weight of occupants, cargo, and baggage. Difference between ramp weight and basic empty weight. Maximum weight approved for ground maneuvering. (It 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 land- ing touchdown. Maximum weight exclusive of usable fuel. January 1978 ) BEECHCRAFT Duchess 76 Loading Condition Reference Datum Station Arm Moment Airplane Center of Gravity (CG) CG Arm CG Limits January 1978 section I General That combination of airplane weight and corresponding moment applicable to the various loadings computed for weight and balance purposes. An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The horizontal distance from the refer- ence datum to the center of gravity (CG) of an item. The product of the weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify ba- lance calculations by reducing the number of digits.) The point at which an airplane would balance if suspended. Its distance from the reference datum is found by divid- ing the total moment by the total weight of the airplane. The arm obtained by adding the air- plane's individual moments and divid- ing the sum by the total weight. The extreme center of gravity locations within which the airplane must be oper- ated at a given weight. 1-19 Section I General Tare Leveling Points Jack Points 1-20 BEECHCRAFT Duchess 76 The apparent weight which may be indi- cated by a scales before any load is applied. 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 pur- poses. January 1978 , ) BEECHCRAFT Duchess 76 SECTION II LIMITATIONS TABLE OF CONTENTS SUBJECT PAGE Airspeed Limitations 2-3 Airspeed Inclic:ator lv1arf(il1~s 2~ Power Plant Limitations 2-4 Engines 2~ Fuel 2-5 Fuel Additives 2-5 Oil. 2-5 Propellers 2-5 Power Plant Instrument lv1arkin~s 2-6 lv1isc:ellaneous Instrument lv1arkings 2-6 Weight Limits '" 2-7 Center of Gravity 2-7 Maneuvers 2-7 Flight Load Factors (3900 Pounds) 2-8 Minimum Flight Crew 2-8 Kinds of Operation 2- 8 Fuel 2-9 Fuel Management 2-9 Seating 2-9 Structural Life 2-9 Required Equipment for Various Conditions of Flight... 2-10 Plac:ards 2-21 September, 1983 2-1 9L6~ ..tnmuer 9l SSa40na J..:j'fl::f::>H0338 >IN'flS l.::I31 A11'fNOI.LN3~NI SUOnB~'W!1 IIUO!~ BEECHCRAFT Duchess 76 Section II limitations The limitations included in this section have been approved by the Federal Aviation Administration. The following limitations in this section must be observed in the operation of this airplane. AIRSPEED LIMITATIONS SPEED CAS lAS REMARKS KTS KTS Never Exceed 194 iJ:194'j Do Not Exceed This Speed in VNE Any Operation, Maximum 154 154"1 Do Not Exceed This Speed Ex- Structural cept in Smooth Air and Then Cruising Only With Caution. VNO Maneuvering 132 19?; Do Not Make Full or Abrupt VA Control Movements Above This Speed. Maximum Flap 110 1JQ;~ Do Not Extend Flaps or Oper- Extension/Extended ate With Flaps Extended VF and VFE Above This Speed. (Full Down 35°) Maximum 140 140\ Do Not Exceed This Speed Landing Gear With Landing Gear Extended. Extended VLE Maximum Do Not Extend or Retract Landing Gear Landing Gear Above This Operating VLO Speed. Extension 140 140 Retraction 113 i1CH:l$ Air Minimum 67 '65'1 Minimum Speed for Directional Control Controllability After Sudden VMCA Loss of Engine . .JClnYJllIyJ.978 2-3 Section II Limitations *AIRSPEED INDICATOR MARKINGS BEECHCRAFT Duchess 76 MARK- CAS VALUE lAS VALUE SlGNIRCANCE ING OR RANGE OR RANGE KTS KTS White Full Rap Arc 58-110 60-110 Operating Range Blue Single-Engine Radial 86 85 Best Rate- of-Climb Red Minimum Radial 67 65 Single-Engine Control (VMCA) Green NormalOperat- Arc 68-154 70-154 ing Range Yellow Operate With Arc 154-194 154-194 Caution, Only In Smooth Air Red Maximum Speed Radial 194 194 For All Operations (Never Exceed) *The airspeed indicator is marked in lAS values. POWER PLANT LIMITATIONS ENGINES Two Avco Lycoming engines installed; one 0-360-A1G6D (clockwise rotating) located on the left Wing, and one LO-360- A1G6D (counterclockwise rotating) located on the right wing. The engines are four-cylinder, direct-drive, horizontally opposed, and each rated at 180 horsepower at 2700 rpm. Take-off and Maximum Continuous Power. , Full Throttle, 2700 RPM Maximum Oil Temperature 245°F Maximum Cylinder Head Temperature 500°F ) 2-4 October 1979 BEECHCRAFT Duchess 76 section II Limitations Minimum Oil Pressure (Idle) 25 psi Maximum Oil Pressure 100 psi Minimum Fuel Pressure 0.5 psi Maximum Fuel Pressure 8.0 psi FUEL Aviation Gasoline, grade 100 (green) or grade 100 LL (blue). FUEL ADDITIVES ALCOR TCP Concentrate, mixed according to the instructions provided by Alcor, Inc. OIL Engine oils must meet Avco Lycoming Specification No. 301 F and be used in accordance with Aveo Lycoming IService Instruction NO.1 014J or subsequent revisions. Refer to the Approved Engine Oils, Section VIII, SERVICING. PROPELLERS Two Hartzell, constant-speed, full-feathering, two-blade pro- pellers: the left engine (clockwise rotating) has an HC-M2YR- 2CEUF hub with FC 7666A blades and C2285-3P spinner; the right engine (counterclockwise rotating) incorporates an HC-M2YR-2CLEUF hub with FJC 7666A blades and a C2285-3LP spinner. Pitch settings at the 3D-inch station: Low, 12.1° + .1°; High, lJO to 20°; Feathered, 81° :!: 1°. Diameter is 76 inches, with cut-off permitted to 74.0 inches. September, 1983 2-5 Section II Limitations BEECHCRAFT Duchess 76 POWER PLANT INSTRUMENT MARKINGS Oil Temperature Caution Range (Yellow Arc) 60 to 120°F Normal Operating Range (Green Arc) 120 to 245°F Maximum (Red Radial) 245°F Oil Pressure Minimum Idle (Red Radial) 25 psi Caution Range (Yellow Arc) 25 to 60 psi Normal Operating Range (Green Arc) 60 to 100 psi Maximum (Red Radial) 100 psi Manifold Pressure Normal Operating Range (Green Arc) 15 to 29.6 in. Hg Tachometer Normal Operating Range (Green Arc) 2000 to 2700 rpm Maximum (Red Radial) 2700 rpm Fuel Pressure Minimum (Red Radial) 0.5 psi Normal Operating Range (Green Arc) 0.5 to 8.0 psi Maximum (Red Radial) 8.0 psi Cylinder Head Temperature Normal Operating Range (Green Arc) 200 to 500°F Maximum (Red Radial) 500°F MISCELLANEOUS INSTRUMENT MARKINGS Instrument Pressure Normal Operating Range (Green Arc) 4.3 to 5.9 in. Hg Red Button Source Failure Indicators 2-6 January 1978 BEECHCRAFT Duchess 76 Section II limitations Fuel Quantity E to 9 Gallons Yellow Arc . WEIGHT LIMITS Maximum Ramp Weight.. 39161bs Maximum Take-off Weight. 3900 Ibs Maximum landing Weight 3900 Ibs Zero Fuel Weight 3500 Ibs Maximum Baggage Compartment Load 200 lbs CENTER OF GRAVITY (landing Gear Extended) Forward Limits: 106.6 inches aft of datum at 3250 lbs and under, then straight line variation to 110.6 inches aft of datum at a weight of 3900 Ibs. Aft Limit: 117.5 inches aft of datum at all weights. Reference Datum: 129.37 inches forward of the center of wing spar jack points. MAC Leading Edge: 99.08 inches aft of datum. MAC Length: 57.65 inches. MANEUVERS This is a normal category airplane. Acrobatic maneuvers, including spins, are prohibited. Maximum slip duration 30 seconds January 1978 2-7 Section II Limitations FLIGHT LOAD FACTORS (3900 POUNDS) BEECHCRAFT Duchess 76 Positive maneuvering load factors: Flaps Up 3.8G Flaps Down (ON) 2.0G Negative maneuvering load factor: Flaps Up -1.52G MINIMUM FLIGHT CREW One pilot KINDS OF OPERATION This airplane is approved for the following type operations when the required equipment is installed and operational as defined herein: 1. VFR day and night 2. IFR day and night 3. FAR 91 operations when all pertinent limitations and performance considerations are complied with. WARNING FLIGHT IN ICING CONDITIONS PROHIBITED. \ 2-8 January 1978 BEECHCRAFT Duchess 76 FUEL Section II Limitations TOTAL FUEL with left and right wing fuel systems full: Capacity " 103 gallons* Usable 100 gallons 31 t"tZ *Value given is nominal. Tank capacity will vary with temper- ature, and manufacturing tolerances. FUEL MANAGEMENT Do not take off when Fuel Quantity indicators indicate in the yellow band on either indicator. Maximum slip duration is 30 seconds. The fuel crossfeed system to be used during emergency conditions in level flight only. SEATING All occupied seats must be in the upright position for takeoff and landing. STRUCTURAL LIFE The basic wing structure has a substantiated life of 20,000 flight hours provided the mandatory inspection requirements of chapter four of the BEECHCRAFT DUCHESS 76 MAINTENANCE MANUAL are complied with. September, 1983 2-9 Section II Limitations BEECHCRAFT Duchess 76 REQUIRED EQUIPMENT FOR VARIOUS CONDITIONS OF FLIGHT Part 91 of the Federal Aviation Regulations specifies minimum numbers and types of airplane instruments and equipment which must be installed and operated for various kinds of flight conditions. This includes VFR day, VFR night, IFR day and IFR night. Regulations also require that all airplanes be certified 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 air- worthiness. If 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 were operable. With appropriate limita- tions, the operation of every system or component installed in the airplane is not necessary when the remaining operative instruments and equipment provide for continued safe opera- tion. Operation in accordance with limitations established to maintain airworthiness can permit continued or uninterrupted operation of the airplane. For the sake of brevity, the Required Equipment Listing does not include obviously required items such as wings, rudder,· flaps, engines, landing gear, etc. Also the list does not include items which do not affect the airworthiness of the airplane such as entertainment systems, passenger convenience items, etc. However, it is important to note that ALL ITEMS WHICH ARE RELATED TO THE AIRWORTHINESS OF THE AIRPLANE AND NOT I NCLUDED ON THE LIST ARE AUTOMATICALLY REQUIRED TO BE OPERATIVE. ,/ 2-10 September, 1983