[fltsim.0] title=MD-83 Continental sim=MD_83 model= panel= sound= texture= kb_checklists=MD_83_check kb_reference=MD_83_ref atc_id=N916CO atc_airline=CONTINENTAL atc_flight_number=478 ui_manufacturer=McDonnell-Douglas/Boeing ui_type=MD-83 ui_variation=Continental Airlines description=The popular MD-80 series is a stretched and improved development of the McDonnell Douglas DC-9. The origins of the MD-80 lie in 1975 testing where a standard DC-9 was fitted with improved, more efficient, higher bypass ratio JT8D200 series turbofans. MDC originally proposed fitting the new engines (which meet Stage 3 noise limits) to a development designated the DC-9-55, which would have featured two JT8D209s and a 3.86m (12ft 8in) stretched fuselage over the 50. Instead MDC developed the DC-9 Super 80 (or DC-9-80), combining the new engines with a further stretched fuselage, increased span wing and other improvements. Launched in October 1977, the Super 80 first flew on October 18 1979. Certification for the initial Super 80 model, the 81, was granted in July 1981. The first customer delivery was to Swissair in September 1980. McDonnell Douglas renamed the DC-9-80 the MD-80 in 1983. The MD-80 designation however is a generic designation for the series and does not apply to a certain model type. The specific MD-80 models are the initial MD81, the MD82 with more powerful JT8D217s, the extended range MD83 with extra fuel and more efficient JT8D219s, and the MD88 (first flight August 1987) with the JT8D219s of the MD83 with an EFIS flightdeck and redesigned cabin interior, with other improvements. The shorter fuselage but longer range MD-87 is described separately under McDonnell Douglas. Initial sales of the Super 80 were slow until American Airlines placed an initial order for 67 MD82s (with options on 100) in early 1984 (American now operates a fleet of 260 MD-80s), kickstarting what went on to become a highly successful program - the 1000th MD-80 was delivered in March 1992. Following the 1997 merger of Boeing and McDonnell Douglas the future of the Douglas airliners were reviewed. In December 1997 Boeing announced its decision to drop the MD-80 and MD-90 once current orders were fulfilled. An April 1998 TWA order for 24 MD-83s will see the MD-80 remain in production until January 2000. atc_heavy=0 [General] atc_type=Boeing atc_model=MD80 editable=0 performance= [WEIGHT_AND_BALANCE] max_gross_weight=160000 // (pounds) empty_weight=79686 // (pounds) reference_datum_position=77.0, 0, 0 // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline) empty_weight_CG_position=-74.0, 0, 0 // (feet) longitudinal, lateral, vertical distance from specified datum max_number_of_stations=50 station_load.0=33000, -69.5, 0.0, 0.0 //Payload Weight (lbs), longitudinal, lateral, vertical positions from datum (feet) ;Moments of Inertia empty_weight_pitch_MOI=1651967 empty_weight_roll_MOI=465681 empty_weight_yaw_MOI=1447094 empty_weight_coupled_MOI=0 [flight_tuning] cruise_lift_scalar=1.0 parasite_drag_scalar=1.0 induced_drag_scalar=1.0 elevator_effectiveness=1.0 aileron_effectiveness=1.0 rudder_effectiveness=1.0 pitch_stability=1.0 roll_stability=1.0 yaw_stability=1.0 elevator_trim_effectiveness=1.0 aileron_trim_effectiveness=1.0 rudder_trim_effectiveness=1.0 [GeneralEngineData] engine_type=1 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop Engine.0=-103.6, -8.5, 0.6 //(feet) longitudinal, lateral, vertical distance from reference datum Engine.1=-103.6, 8.5, 0.6 //(feet) longitudinal, lateral, vertical distance from reference datum fuel_flow_scalar=1.0 //Scalar for fuel flow efficiency [TurbineEngineData] fuel_flow_gain=0.002 //Gain on fuel flow inlet_area=10.4 //Square Feet, engine nacelle inlet area rated_N2_rpm=29920 //RPM, second stage compressor rated value static_thrust=21000 //Lbs, max rated static thrust at Sea Level afterburner_available=0 //Afterburner available? reverser_available=1 //Thrust reverser available? [jet_engine] thrust_scalar=1.0 [electrical] ;BusType, MaxAmpLoad, MinVoltage BusTypes:0=MainBus,1=AvionicsBus,2=BatteryBus,3=HotBatteryBus,4-7=Generator/AlternatorBus(1-4) flap_motor=0, 5 , 17.0 gear_motor=0, 5 , 17.0 autopilot=0, 5 , 17.0 avionics_bus=0, 10, 17.0 avionics=1, 5 , 17.0 pitot_heat=0, 2 , 17.0 additional_system=0, 20, 17.0 marker_beacon=1, 2 , 17.0 gear_warning=0, 2 , 17.0 fuel_pump=0, 5 , 17.0 starter1=0, 20, 17.0 light_nav=0, 5 , 17.0 light_beacon=0, 5 , 17.0 light_landing=0, 5 , 17.0 light_taxi=0, 5 , 17.0 light_strobe=0, 5 , 17.0 light_panel=0, 5 , 17.0 //0 Class <0=none,1=wheel, 2=scrape, 3=float> //1 Longitudinal Position (feet) //2 Lateral Position (feet) //3 Vertical Position (feet) //4 Impact Damage Threshold (Feet Per Minute) //5 Brake Map (0=None, 1=Left, 2=Right) //6 Wheel Radius (feet) //7 Steer Angle (degrees) //8 Static Compression (feet) (0 if rigid) //9 Max/Static Compression Ratio //10 Damping Ratio (0=Undamped, 1=Critically Damped) //11 Extension Time (seconds) //12 Retraction Time (seconds) //13 Sound Type //14 Airspeed limit for retraction (KIAS) //15 Airspeed that gear gets damage at (KIAS) [contact_points] point.0=1, -9.20, 0.00, -8.0, 1500, 0, 1.08, 68.0, 1.00, 2.5, 0.9, 7.0, 5.0, 0, 190, 250 point.1=1, -83.10, -8.33, -9.4, 3000, 1, 1.85, 0.0, 1.50, 2.5, 0.8, 7.0, 7.0, 2, 190, 250 point.2=1, -83.10, 8.33, -9.4, 3000, 2, 1.85, 0.0, 1.50, 2.5, 0.8, 7.0, 7.0, 3, 190, 250 point.3=2, -95.75, -53.92, -1.0, 1200, 0, 0.00, 0.0, 0.00, 0.0, 0.0, 0.0, 0.0, 5 point.4=2, -98.75, 53.92, -1.0, 1200, 0, 0.00, 0.0, 0.00, 0.0, 0.0, 0.0, 0.0, 6 point.5=2, -139.00, 0.00, 3.0, 1200, 0, 0.00, 0.0, 0.00, 0.0, 0.0, 0.0, 0.0, 9 point.6=2, -3.00, 0.00, 0.0, 1200, 0, 0.00, 0.0, 0.00, 0.0, 0.0, 0.0, 0.0, 4 max_number_of_points=21 static_pitch=-0.9 //degrees, pitch when at rest on the ground (+=Up, -=Dn) static_cg_height=7.9 //feet, altitude of CG when at rest on the ground [Views] eyepoint=-13.3, -1.82, 5.0 //(feet) longitudinal, lateral, vertical distance from reference datum [flaps.0] type=1 // 1 - tail, 2 - lead span-outboard=0.8 // 0.0 .. 1.0 extending-time=20 // seconds flaps-position.0=0 // degrees, KIAS flaps-position.1=10 // degrees, KIAS flaps-position.2=20 // degrees, KIAS flaps-position.3=30 // degrees, KIAS flaps-position.4=40 // degrees, KIAS damaging-speed=250 // KIAS blowout-speed=300 // KIAS [pitot_static] vertical_speed_time_constant=1 //Increasing this value will cause a more instantaneous reaction in the VSI [LIGHTS] //Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit, 5=landing light.0=3, -96.00, 53.70, -0.60, fx_navgrem , light.1=3, -96.00, -53.70, -0.60, fx_navredm , light.2=2, -96.50, -54.20, -0.60, fx_strobeh , light.3=2, -96.50, 54.20, -0.60, fx_strobeh , light.4=4, -12.00, 0.00, 4.50, fx_vclighth , [exits] number_of_exits=2 exit_rate.0=0.4 ;Percent per second exit_rate.1=0.4 ;Percent per second [SMOKESYSTEM] smoke.0=0.6,-110.6,-8.5, fx_smoke_rx smoke.1=0.6,-110.6,8.5, fx_smoke_rx [EFFECTS] wake=fx_wake water=fx_spray dirt=fx_tchdrt concrete=fx_sparks touchdown=fx_tchdwn, 1 [fuel] Center1=-76.2, 0.0, -6.0, 580.0, 3.0 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) Center2=-78.2, 0.0, -6.0, 580.0, 3.0 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) LeftMain=-78.7, -12.1, -4.0, 2920.0, 3.0 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) RightMain=-78.7, 12.1, -4.0, 2920.0, 3.0 //Longitudinal (feet), Lateral (feet), Vertical (feet), Usable(gallons), Unusable (gallons) fuel_type=2 //Fuel type: 1 = Avgas, 2 = JetA number_of_tank_selectors=1 [airplane_geometry] wing_area=1209.0 //Square feet wing_span=107.8 //Feet wing_root_chord=23.1 //Feet wing_dihedral=3.0 //Degrees wing_incidence=1.3 //Degrees wing_twist=0.0 //Degrees oswald_efficiency_factor=0.8 //Measure of lift effeciency of wing wing_winglets_flag=0 //Are winglets available? wing_sweep=24.5 //Degrees, wing leading edge wing_pos_apex_lon=-61.0 //Feet, longitudinal distance from reference point, negative going aft wing_pos_apex_vert=0.0 //Feet, vertical distance from reference point, positive going up htail_area=341.0 //Square feet htail_span=40.0 //Feet htail_pos_lon=-134.0 //Feet, longitudinal distance from reference point, negative going aft htail_pos_vert=0.0 //Feet, vertical distance from reference point, positive going up htail_incidence=0.0 //Degrees htail_sweep=30.0 //Degrees, horizontal tail leading edge vtail_area=168.0 //Square feet vtail_span=14.8 //Feet, tip to body vtail_sweep=25.0 //Degrees, vertical tail leading edge vtail_pos_lon=-131.8 //Feet, longitudinal distance from reference point, negative going aft vtail_pos_vert=10.9 //Feet, vertical distance from reference point, positive going up elevator_area=145.0 //Square feet aileron_area=38.0 //Square feet rudder_area=65.3 //Square feet elevator_up_limit=26.0 //Degrees elevator_down_limit=26.0 //Degrees aileron_up_limit=30.0 //Degrees aileron_down_limit=30.0 //Degrees rudder_limit=30.0 //Degrees elevator_trim_limit=20.0 //Degrees spoiler_limit=60.0 //Degrees spoilerons_available=1 //Spoilerons Available? aileron_to_spoileron_gain=3 //Aileron to spoileron gain min_ailerons_for_spoilerons=10 //Degrees min_flaps_for_spoilerons=0 //Minimum flap handle position when spoilerons activate [Reference Speeds] flaps_up_stall_speed=142.0 //Knots True (KTAS) full_flaps_stall_speed=113.6 //Knots True (KTAS) cruise_speed=437.7 //Knots True (KTAS) [keyboard_response] //Breakpoint speeds (knots) on the keyboard increments of control surfaces. //Speed at which the incremenet is reduced to 1/2 and 1/8 respectively. elevator=150.0, 250.0 aileron=150.0, 250.0 rudder=150.0, 250.0 [autopilot] autopilot_available=1 flight_director_available=1 default_vertical_speed=1000.0 autothrottle_available=1 autothrottle_arming_required=1 autothrottle_max_rpm=90 autothrottle_takeoff_ga=1 pitch_takeoff_ga=8; use_no_default_pitch=1 use_no_default_bank=1 [forcefeedback] gear_bump_nose_magnitude=3000 ; 0 - 10000 gear_bump_nose_direction=18000 ; 0 - 35999 degrees gear_bump_nose_duration=250000 ; in microseconds gear_bump_left_magnitude=2700 ; 0 - 10000 gear_bump_left_direction=35500 ; 0 - 35999 degrees gear_bump_left_duration=250000 ; in microseconds gear_bump_right_magnitude=2700 ; 0 - 10000 gear_bump_right_direction=00500 ; 0 - 35999 degrees gear_bump_right_duration=250000 ; in microseconds ground_bumps_magnitude1=1300 ; 0 - 10000 ground_bumps_angle1=08900 ; 0 - 35999 degrees ground_bumps_intercept1=3.0 ground_bumps_slope1=0.20 ground_bumps_magnitude2=200 ; 0 - 10000 ground_bumps_angle2=09100 ; 0 - 35999 degrees ground_bumps_intercept2=1.075 ground_bumps_slope2=0.035 crash_magnitude1=10000 ; 0 - 10000 crash_direction1=01000 ; 0 - 35999 degrees crash_magnitude2=10000 ; 0 - 10000 crash_direction2=9000 ; 0 - 35999 degrees crash_period2=75000 ; in microseconds crash_duration2=2500000 ; in microseconds [direction_indicators] direction_indicator.0=3,0
