Lancair Columbia 400 Information Manual
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Contents
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Section 5Performance Columbia 400 (LC41-550FG)RC050002 Initial Issue of Manual: November 10, 20045-34 Latest Revision Level/Date: -/11-10-2004SAMPLE PROBLEMAirplane ConfigurationTakeoff Weight ... 3600 lbs. (1633 kg) Maximum Gross WeightUsable Fuel .................................................. 98 Gallons (371 L)Cruise EnvironmentDistance of Trip......................................... 412 Nautical MilesPressure Cruise Altitude ..........................................8000 FeetCruise Power ......................................... 80% BHP/2500 RPMAmbient Air Temperature ............................ -1°C (Standard)En Route Winds ...................................... 30 Knot HeadwindTakeoff EnvironmentAirport Pressure Altitude ........................................ 3500 FeetAmbient Air Temperature ......... 25°C (17°C above standard)Headwind Component ............................................. 30 KnotsRunway Length ...................................................... 3000 FeetObstacle at the end of the runway ................................ 50 FeetClimb to Cruise Altitude................... Max. Continuous PowerLanding EnvironmentAirport Pressure Altitude ........................................ 2000 FeetAmbient Air Temperature ...... 30°C (16.5°C above standard)Landing Runway Number .................................................. 36Wind Direction & Velocity ......................... 040º at 25 KnotsRunway Length ...................................................... 3000 FeetObstacle at approach end of the runway.......................... NoneSOLVE FOR THE FOLLOWING ITEMSNo. Item Solution Comments1. What is the takeoff ground rundistance at the departure airport? 1150± Feet Problem is different than example arrows, i.e., takeoffweight - 3600 lbs. and headwind - 30 knots.2.What is the total takeoff distanceat the departure airport (groundrun and obstacle clearance)?1750± Feet Major indices are 200 feet and minor indices (notprinted on the graph) are 100 feet.3.Assume a climb to cruisealtitude is started at a pressurealtitude of 4000 feet. What is theapproximate fuel used to reachcruise altitude?1.7 Gallons(6.4 L)The fuel required to reach a pressure altitude of 4000and 8000 feet is 1.7 and 3.4 gallons, respectively. Thedifference between these two altitudes yields 1.7gallons. No adjustment for non-standard temperatureis possible.4.What distance over the ground iscovered in the climb under nowind conditions.? What is theapproximate time?6 NM2.9 MinutesUsing the technique described in No. 3 subtract the4000 pressure altitude distance/time from the 8000pressure altitude distance/time.5. What is the fuel flow at the 8000foot cruise altitude?22 GPH(83 LPH) Taken directly from chart.6.What is the true airspeed at the8000 foot cruise altitude (to thenearest whole knot)?195 knots Taken directly from chart.7.Using the cruise and rangeprofiles, what are theapproximate miles covered andtime aloft at 80% BHP?715 NM3.6 HoursNotice that range and endurance are significantlyreduced when operating at higher power settings.8.Assume a 500 FPM descent isused for arrival at the destinationairport. At what distance fromthe airport should the descentbegin to arrive at 1000 feetabove the surface?33 NMThe airport elevation is 2000 feet and the descent isfrom 8000 feet; hence, calculations should compare8000 feet with 3000, which is 1000 feet above thesurface. See the instruction on page 5-31 for descentsto airports above sea level.9.What are the crosswind andheadwind components at thedestination airport?16 kts xwind19 kts hdwndThe wind is 40º off the runway centerline. See Figure5 - 9 for a detailed explanation.10.What is the landing distancerequired at the destinationairport, with landing flaps, atmaximum landing weight?1100± FeetIn No. 10 above, the headwind component is 19 knots.Insert this information along with the airport elevationand temperature into Figure 5 - 32. |
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