Lancair Legacy Pilot'S Operating Handbook And Flight Manual Download

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I-8

February 2008

Legacy

I-9

February 2008

Legacy

OIL CAPACITIES

IO-540-V4A5....................................... 8 quarts (U.S.)
IO-550-N.............................................. 8 quarts (U.S.)

CABIN AND ENTRY DIMENSIONS

Length - 45”
Height - 42.5”
Width - 41”

BAGGAGE

Compartment Volume: 11 ft.

SPECIFIC LOADINGS (Max Take-off Wt)

Wing Loading:

At 2,200 lbs: 26.7 lbs./sq.ft.

Power Loading:

At 2,200 lbs.:

Lycoming IO 540 V4A5: ............ 8.5 lbs./hp
Contenintal IO 550-N: .............. 7.1 lbs/hp

*Rudder Pedals all the way Forward

Summary of Contents for Legacy

Page 1: ...he Owners will need to develop a Pilot s Operating Handbook as part of the aircraft airworthiness process and are encouraged to modify this document to help in that process Mfgr s Serial No ___________________________ Registration No ___________________________ LEGACY ...

Page 2: ...Legacy Published by Lancair International Inc Redmond Oregon 97756 Authorized Dealer Neico Aviation Inc 2244 Airport Way Redmond Oregon 97756 ...

Page 3: ...iii February 2008 Legacy PAGES DESCRIPTION PILOT S OPERATING HANDBOOK and AIRPLANE FLIGHT MANUAL February 2008 Log of Revisions ...

Page 4: ... periodic review of good piloting techniques for this aircraft This manual will not replace safe flight instruction or good piloting techniques NOTE Owner modifications to your Lancair may alter the applicability of this handbook which meets the GAMA specification 1 for pilots operating handbooks WARNING Use only genuine Lancair approved parts obtained from authorized Lancairdealers when repairing...

Page 5: ...ON II LIMITATIONS SECTION III EMERGENCY PROCEDURES SECTION IV NORMAL PROCEDURES SECTION V PERFORMANCE SECTION VI WEIGHT AND BALANCE EQUIPMENT LIST SECTION VII SYSTEM DESCRIPTIONS SECTION VIII HANDLING SERVICING MAINTENANCE SECTION IX SUPPLEMENTS SECTION X SAFETY INFORMATION ...

Page 6: ...Legacy ...

Page 7: ... DESCRIPTIVE DATA I 8 ENGINES I 8 PROPELLERS I 8 FUELS I 8 OIL CAPACITIES I 9 CABIN AND ENTRY DIMENSIONS I 9 BAGGAGE I 9 SPECIFIC LOADINGS MAX TAKE OFF WT I 9 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS I 10 METEOROLOGICAL TERMINOLOGY I 11 POWER TERMINOLOGY I 11 ENGINE CONTROLS INSTRUMENTS I 11 AIRPLANE PERFORMANCE FLIGHT PLANNING TERMINOLOGY I 12 WEIGHT AND BALANCE TERMINOLOGY I 12 NOTES I 14 ...

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Page 9: ...k and Airplane Flight Manual as well as any placards located in the airplane Again another reminder the operator should also be familiar with the FederalAvia tion Regulations as applicable to the operation and maintenance of experimental aircraft and FAR Part 91 General Operating and Flight Rules The aircraft should be operated and maintained in accordance with any FAAAirworthiness Directives whic...

Page 10: ...re Indicated Airspeeds IAS in Knots and assume zero instrument error In an effort to provide as complete coverage as possible of the Lancair Legacy some optional equipment has been included in the scope of this handbook However due to the variety of airplane configurations available some equipment described and depicted herein may not be included on your specific airplane The following information...

Page 11: ... a box containing 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 Revisions will be issued All Logs of Revisions must be retained in the handbook to provide a current record of material status until a reissue is made WARNING When...

Page 12: ...w or revised supplement compare the Log of Revisions page just received with the existing Log page in the manual Retain only the new page with the latest date on the bottom of the page and discard the old one Absolute Minimum Turning Radius 17 5 34 10 ...

Page 13: ...ary 2008 Legacy LEGACY THREE VIEW SIDE VIEW y x FRONT VIEW Aircraft Length x for 550 270 25 for 540 274 Aicraft Height y for 550 88 25 for 540 90 5 25 8 Note Above dimension includes strobe lights TOP VIEW 50 34 ...

Page 14: ...ropellers for the Continental IO 550 N BHC J2YF 1BF F7694 4TX This is a 2 blade constant speed 69 diameter propeller MTV 9 D 183 109 This is a 3 blade constant speed composite 72 diameter propeller Note the larger diameter and keep in mind the ground clearance is reduced by 1 1 2 Propellers for the Lycoming IO 540 V4A5 HC F2YR 1F F7694 4T This is a 2 blade constant speed 69 diameter propeller NOTE...

Page 15: ...BIN AND ENTRY DIMENSIONS Length 45 Height 42 5 Width 41 BAGGAGE Compartment Volume 11 ft 3 SPECIFIC LOADINGS Max Take off Wt Wing Loading At 2 200 lbs 26 7 lbs sq ft Power Loading At 2 200 lbs Lycoming IO 540 V4A5 8 5 lbs hp Contenintal IO 550 N 7 1 lbs hp Rudder Pedals all the way Forward ...

Page 16: ...ynamic control will not overstress the airplane VFE Maximum Flap Extend Speed is the highest speed permissible with wing flaps in a prescribed extended position VLE Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended VLO Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely exte...

Page 17: ...arometric subscale has been set to 29 92 inches Hg or 1013 2 millibars Station Pressure Actual atmospheric pressure at field elevation Wind The wind velocities recorded as variables on the charts of this hand book are to be understood as the headwind or tailwind components of the reported winds POWER TERMINOLOGY Take off and Maximum Continuous The highest power rating not limited by time Cruise Cl...

Page 18: ...onstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during take off and landing was actually demonstrated The value shown is considered to be limiting The value in this hand book is that demonstrated by Lancair test pilots and considered safe MEA Minimum enroute IFR altitude Route Segment A part of a route Each end of that part is iden...

Page 19: ...el Fuel remaining after a runout test has been completed Standard Empty Weight Weight of a standard airplane including unusable fuel full operating fluids and full oil Basic Empty Weight Standard empty weight plus any optional equipment Useful Load Difference between take off weight or ramp weight if applicable and basic empty weight Maximum Take off Weight Maximum weight approved for the start of...

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Page 23: ... BY IO 540 V4A5 ENGINE II 4 FUEL GRADES AVIATION GASOLINE II 5 OIL SPECIFICATION II 5 HYDRAULIC PRESSURE II 6 WEIGHT LIMITS II 6 CENTER OF GRAVITY LIMITS II 6 MEAN AERODYNAMIC CHORD II 6 MANEUVER LIMITS II 6 DEMONSTRATED MANEUVERS II 7 FLIGHT LOAD FACTOR LIMITS II 7 TYPES OF OPERATIONS AND LIMITS II 8 FUEL QUANTITIES II 8 FUEL MANAGEMENT II 8 SEATING II 9 WINTER OPERATIONS II 9 PLACARDS II 9 NOTES...

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Page 25: ...ative that you calibrate your airspeed system static and pitot to provide the corrections to the values shown below in KCAS If there is instrument gauge error that needs to be factored in also to reach KIAS AIRCRAFT OPERATING SPEEDS Lancair Legacy SPEED MARKING KCAS Never Exceed Speed VNE Red Line 274 Maneuvering Speed VA 170 Gross 2200 lbs 158 1900 lbs 140 1500 lbs Normal Oper Range VNO Green Arc...

Page 26: ...takeoff and cruise capabilities for example Lancair Legacy Powered by IO 550 N Engine Specification Max Continuous RPM 310 hp at 2700 rpm 77 Cruise 240 hp at 2500 rpm Cylinder Heat Temperatures Maximum short time period 460 F 238 C Recommended Max Temperature Cruise 380 F Oil Temperatures Maximum 240 F 115 C Normal 170 F 200 F Minimum take off 100 F Oil Pressure Maximum cold 100 psi Normal Operati...

Page 27: ...perating Range 4 8 5 2 in Hg FUEL GRADES Aviation Gasoline Only 100LL Blue in Color OIL SPECIFICATION Follow the engine manufacturer s recommendations Following initial break in of the engine it should be operated with an ashless dispersant oil MIL L 22851 conforming to the applicable engine handbook Break in the first 50 hours or until oil consumption has stabilized should be accomplished using a...

Page 28: ...amic chord Refer to section VI for the weight and balance instructions MANEUVER LIMITS The Lancair Legacy is licensed as EXPERIMENTAL Spins are not recommended Aerobatic maneuvers which have been flown by Lancair test pilots are shown in the chart below Care must be used and smooth control inputs used at all times when performing aerobatics and instruction in the maneuvers is considered virtu ally...

Page 29: ...opellerto go to flat pitch and engine overspeed will result Transient oil pressure conditions near zero must be limited to less than two 2 seconds NOTE Speeds shown are calibrated Corrections must be applied from a calibration of your aircraft to determine your proper entry indicated airspeeds All pilots are again reminded that instruction in aerobatics in the Lancair is highly desirable Speed bui...

Page 30: ...tor valve installed in the center console allows you to select between the left or tight tanks or shut the fuel off Wing tank selection is typically managed by switching every 30 minutes to keep the aircraft within trim The electric fuel boost pump is used for starting the engine high boost The pri mary difference between the Lycoming and Continental fuel systems is the use of a single stage elect...

Page 31: ...requirements should be placed where obvious and made clearly understandable An example of this would be the gear emergency extension procedure It should be placed appropriately near the gear dump valve as well as being available in the EMERGENCY Section of this handbook Red Tab An example of a switch marking is the strobe light switch It should be labled as Strobe with On and Off positions identif...

Page 32: ... some recommended placards In front of the pilot Airspeed Limitations Max Lndg Gear Ext Speed 140 Kts Max Flap Ext Speed 10 170 Kts Max Full Flaps 120 Kts Near the fuel gauges OR fuel transfer pumps Gallons Gallons Usable Usable Emergency landing gear extension near gear Maximum 90 KIAS Gear CB Gear Relay OUT Gear Switch DOWN Gear Dump Valve OPEN Gear 3 lights Gear Dump Valve CLOSED ...

Page 33: ...N FLIGHT These placards can be photocopied and laminated if desired and then pasted in a desirable location by the owner It is recommended that all switches and circuit breakers also be labeled and a dymo marker works well for that task Further it is desirable to place all labels and placards such that all text is visible by the pilot when sitting in the cockpit seat Seat belt must be installed an...

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Page 37: ...G ENGINE III 4 ENGINE FIRE III 5 IN FLIGHT III 5 ON GROUND ENGINE START OR TAXI III 5 EMERGENCY DESCENT III 6 MAX GLIDE CONFIGURATION III 6 LANDING EMERGENCIES III 6 SYSTEMS EMERGENCIES III 7 PROPELLER OVERSPEED III 7 PROPELLER DAMAGE III 7 ELECTRICAL SYSTEM FAILURE III 7 SPEED BRAKES III 8 LANDING GEAR III 9 UNLATCHED CANOPY IN FLIGHT III 9 SPINS III 10 EMERGENCY SPEED REDUCTION III 10 NOTES III ...

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Page 39: ...check lists are presented to capture in a compact format those pilot tasks requiring rapid action These check lists should be kept handy for ready access by the pilot and he should familiarize him her self with them before flying the aircraft Knowledge of the switch control gauge etc location quickly even blindfolded is highly desirable Cockpit time prior to ever flying or after an absence is time...

Page 40: ...e FULLEST TANK Mixture RICH Magneto Cycle return to BOTH Flaps when on final FULL Note With gear down maintain 110 KIAS In Flight Establish 120 KIAS GLIDE Climb to reduce speed if practical Pick LANDING SITE Attempt AIR START Low boost fuel pump ON Fuel Valve FULLEST TANK Mixture RICH Mags Cycle return to BOTH Note If there is not a low boost installed temporarily use a high boost If stopped engag...

Page 41: ...tch OFF All Radios lights etc OFF If fire smell clears turn master switch ON then each item of equipment one at a time waiting long enough to isolate cause If no smell assume an unknown source and Land as soon as possible find and correct the cause If fire continues Throttle IDLE Mixture CUT OFF Fuel Shut off Valve OFF Fuel Pump OFF Transponder 7700 Radio EMERGENCY LOCATION Use active frequency or...

Page 42: ...ablished for your individual aircraft LANDING EMERGENCIES Landing without power When landing site is selected and committed to landing the following checklist can be completed The use of gear UP versus gear DOWN is a function of the landing site If the landing is to be made on water a foamed runway or the sod adjacent to a runway the gear would generally be best left up If the terrain is harsh the...

Page 43: ...ant i e over 200 rpm over redline an engine inspection is called for upon landing Engine operation for the balance of the flight must be monitored closely PROPELLER DAMAGE As with any major component of an aircraft the propeller demands proper care Nicks scratches and other types of damage require care While the construction varies all are highly stressed and these nicks cause stress concentration...

Page 44: ...her anomaly caused by the first difficulty NOTE Each aircraft electrical system varies Your aircraft may be equipped with back up batteries and or alternators Know your electrical system and adapt your emergency procedures accordingly SPEED BRAKES The Precise Flight speed brakes are designed such that it is impossible for one to deploy and remain fully deployed while the other is down If you exper...

Page 45: ...r tower or aircraft can be used to confirm its full down posi tion WARNING Aircraft observers must be used with caution as not all pilots have the training to safely fly formation and may not be sufficiently familiarwith the Lancair gear to confirm its down and locked configuration Once lowered it is not advisable to attempt a retraction prior to landing and deter mining the cause of its failure t...

Page 46: ...out of no more than 4 5 g s taking particular care not to reenter an accellerated stall and another spin WARNING The Legacy is aerodynamically very clean and thus can lose a lot of altitude with such maneuvers EMERGENCY SPEED REDUCTION In an emergency the landing gear can be used to assist in reducing the speed of the aircraft quickly Gear extension should be accompanied by idle power Athorough ge...

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Page 49: ...KS CHECKLIST IV 12 TAKE OFF CLIMB CHECKLIST IV 12 CRUISE CHECKLIST IV 13 GENERAL LEANING RULES IV 13 LEANING EXHAUST GAS TEMPERATURE IV 14 LEANING FLOWMETER IV 14 LEANING MANUAL MIXTURE CONTROL IV 14 USE OF CARBURETOR HEAT ALTERNATE AIR IV 15 ADDITIONAL CHECKLISTS IV 15 DESCENT CHECKLIST IV 15 PRE LANDING CHECKLIST IV 15 BALKED LANDING CHECKLIST IV 16 AFTER LANDING CHECKLIST IV 16 SHUTDOWN CHECKLI...

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Page 51: ...ctly calibrated and account for those errors as necessary NOTE Best airspeeds will vary based on individual aircraft Max Demonstrated X WIND Component 25 KIAS Take off Speeds Rotation 60 KIAS Best Angle of Climb VX 102 KIAS Best Rate of Climb Vy 135 KIAS Cruise Climb 145 KIAS Landing Approach Flaps DOWN 95 KIAS Flaps UP 105 KIAS NOTE Best angle and best rate speeds are for gear up and flaps up ...

Page 52: ...2008 Legacy 1 2 3 4 Oil Door Wing Tip Lights Aileron Trim Tab Speed Brake Static Port NOTE There may be one at the same location in the right side Elevator Trim Tab Flaps Right Wing Left Wing Cockpit Rudder Trim Tab ...

Page 53: ...Visually inspect oleo strut for leaks Visually inspect the over centerlinkage and the hydrau lics Look for leaks Inspect the set screw of the sequence valve 2 Brake Pads CHECK condition 3 Brake Line CHECK condition 4 Gear Doors CHECK condition There shouldd be no cracks Carefully inspect the inboard gear door hinge for cracks 5 Pitot Tube REMOVE cover check for obstruc tions 6 Fuel Drain DRAIN as ...

Page 54: ...in installed There must be no play in trim tab 17 Left Flap CHECK for movement and security CHECK that hinge pins have circlip properly install and the safety wire 3 Empennage 1 Static Port CHECK for blockage 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security No rubbing 4 Trim Tabs The hinge pins must be secure Verify the cotter pins of the trim tab actuator arms ...

Page 55: ...ECURE 9 Fuel Quantity CHECK visually for desired level 10 Wing Tie Down DISCONNECT 11 Fuel Drain DRAIN as necessary NOTE Two drains per wing 12 Gear Doors CHECK condition There should be no cracks Carefully inspect the inboard gear door hinge for cracks 13 Brake Line CHECK condition 14 Brake Pads CHECK condition 15 Main Gear and Tire CHECK for proper inflation and gen eral condition Visually inspe...

Page 56: ...ropeller CHECK condition CAUTION See propeller manufacturer s instructions for nick and damage treatments and limitation Damaged propellers are dangerous failures can be catastrophic 7 Spinner CHECK condition Must be secure No cracks at attach screws 8 Oil Quantity CHECK level 9 Dip Stick SECURE 10 Inspection Door CLOSE SECURE BEFORE STARTING Checklist 1 Baggage Stowed loose items SECURED 2 Rudder...

Page 57: ...adios Avionics ON as required 16 Mixture LEAN during taxi to help avoid plug fouling COLD STARTING Cold starts are similar to normal starts except that more fuel may be required For temperatures below 0 F preheating of the engine may be desirable as well as use of a warm battery Care must be used to limit operation of the starter motor to 30 seconds for each 4 minutes of time to allow internal win...

Page 58: ...een starting attempts and avoid long continuous periods of cranking as damage to the starter will result NOTE In some cases with the Lycoming the flooded engine procedure may work well for starting a hot engine WARNING Should a backfire occur during any start continue cranking to draw any fire back into the engine If backfiring continues or an engine compartment fire starts shut down and EXIT the ...

Page 59: ...ECK Lycoming Max 175 rpm drop 50 rpm difference Continental Max 150 rpm drop 50 rpm difference 8 Throttle IDLE then 1000 rpm 9 Suction CHECK 4 8 5 2 in Hg BEFORE TAKE OFF Checklist 1 Canopy LOCKED recheck 2 Seat Belts Harness SECURE 3 Instruments CHECK 4 Fuel Quantity CHECK 5 Oil Press Temp CHECK GREEN 6 Breakers IN 7 Master Switch ON 8 Avionics Master ON 9 Radios ON SET 10 Auto Pilot OFF 11 Trans...

Page 60: ...WLEDGED 6 Takeoff Runway CLEAR 7 Time Off NOTE TAKE OFF CLIMB Checklist 1 Take off Power 2700 RPM 2 Oil Temperature 100 F MINIMUM 3 Cylinder Head Temperatures 150 F MINIMUM 4 After Power Application CHECK Engine Instruments 5 Check Flight Instruments OPERATING 6 Rotate 65 75 KTS 7 Initial Climb to 1000 120 KTS 8 Positive Climb GEAR UP 9 Alt 800 feet AGL FLAPS UP 10 Reduce RPM 2500 RPM 11 Mixture L...

Page 61: ...435 F 224 C during high performance cruise operations and below 400 F 205 C for economy cruise powers C Maintain Full Rich for Take off and climb For take off from high altitude airports if engine roughness is noted lean only enough to obtain smooth op eration Be alert for temperature rise This is most likely to occur at altitudes over 5000 feet Consult engine manufacturer s recommendations for cr...

Page 62: ...GT Lycoming Lean to 50 F Rich of peak EGT LEANING FLOWMETER Lean to the applicable fuel flow tables or lean to an indication marked for correct fuel flow for each power setting LEANING MANUAL MIXTURE CONTROL Carbureted Engines 1 Slowly move mixture control from Full Rich position towards lean po sition 2 Lean until engine roughness is observed 3 Enrich until engine runs smoothly and power is regai...

Page 63: ...m Those provided herein for the Lancairs are for your convenience Modifications may be required for your particular aircraft DESCENT Checklist 1 Fuel Selector AS DESIRED 2 Fuel Pump OFF 3 Altimeter SET FOR BARO OR FlELD ELEVATION 4 Mixture ENRICHEN THRU DESCENT OR FULL RICH 5 Power AS REQ D Use caution avoid rapid and excessive cooling 6 CHTs MAINTAIN greater than 180 F 7 Ram Air if equipped CLOSE...

Page 64: ...DBY 4 Lights AS REQUIRED 5 Trim RESET FOR TAKE OFF 6 Canopy Seal OFF 7 Time NOTE SHUTDOWN Checklist At parking site 1 Radios OFF 2 Avionics Master OFF 3 Throttle IDLE 4 Mixture IDLE CUT OFF 5 Mags After engine stops OFF 6 Lights OFF 7 Master Switch OFF 8 Chocks Tiedown SECURE ABBREVIATED TAKE OFF CHECKLIST C I G A R T I P Controls FREE AND CORRECT Instruments Gear Switch DOWN Circuit Breakers IN A...

Page 65: ...F Run up Brakes SET Nose wheel Straight Mag Check Lycoming 1800 RPM 175 max each 50 rpm difference Continental 1800 RPM 150 max each 50 rpm difference Propeller 2 CYCLES Oil Pressure IN GREEN Trim Aileron trim Neutral Rudder trim Set for takeoff Elevator trim Set for takeoff Interior Seat belts FASTENED Canopy LATCHED Propeller FULL RPM Autopilot OFF Speedbrakes RETRACTED ...

Page 66: ...nspect the structural integrity of the unit periodically Initial opera tion of the system for the winter months should always include such an inspection A monitoring system should be considered for the cabin air These simple devices change color upon exposure to CO They are quite cheap and excellent insurance against the effects of this odorless colorless and deadly gas Optionally install an elect...

Page 67: ...The engine is warm enough for take off when the throttle can be opened without faltering Take off with a turbocharged engine should not be started if indicated lubricating oil pressure due to cold temperatures is above maximum Excessive oil pressure can cause overboost and consequent engine damage CRUISE OPERATION Cold weather cruise operation may require an occasional cycle of the propeller contr...

Page 68: ...e necessary to overfly do so at reduced power if prudent and overfly at 2000 feet AGL or higher NOTE The above suggestions are recommended where they do not conflict with weather conditions ATC clearances or instructions or where in the judgment of the pilot they can be complied with safely No flyover noise level has been established for these Lancair aircraft as defined by FAR 36 requirements nor...

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Page 71: ... TOWER PASS CALIBRATIONS V 4 PACER CALIBRATIONS V 4 TRAILING CONE CALIBRATION V 5 AIRSPEED SYSTEM CALIBRATION V 7 STALL SPEEDS V 10 TAKEOFF DISTANCES V 12 RATE OF CLIMB V 14 CRUISE SPEEDS V 15 OTHER CHARTS V 15 SUMMARY V 15 CRUISE SPEED DATA V 16 INTERNATIONAL STANDARD ATMOSPHERE V 18 TEMPERATURE CONVERSION V 19 NOTES V 20 ...

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Page 73: ...ty of the static source can be critical to the systems accuracy Most importantly indicated altitude is affected This in turn affects calibrated airspeed i e indicated airspeed corrected for errors due to both the location of the pitot and static port s on the aircraft ALTIMETER CORRECTIONS Static source errors result in altimeter errors and indicated airspeed errors An airspeed indicator is essent...

Page 74: ...rcraft indicated altitude versus true tower altitude can be determined Extreme care should be used when flying such passes particularly the low speed and dirty passes The minimum recommended fly by speed is 80 kts and cool smooth early morning air is best for calm air and traffic reasons The data should be plotted and a smooth curve faired to extrapolate data to the lower speeds A cooperative towe...

Page 75: ...rs Since the Cone provides true outside pressure altitude a differential pressure gauge between the Cone and the aircraft s system will display the error This eliminates the error associated with the comparison of two absolute measurements but requires the use of tables of pressures versus altitudes in the range of inches of water for the altitudes flown The result is however an extremely accurate...

Page 76: ...00 220 240 260 280 300 100 80 60 40 20 0 20 40 60 80 100 ALTIMETER CORRECTION Owners Calibration Flaps and Gear Down Flaps and Gear Up Cruise configuration Altimeter Correction Chart Correction to be Added Feet Indicated Airspeed Knots 60 80 100 120 140 ...

Page 77: ...er on the ac companying charts and tagged as to flap position up approach and full typically and gear position or presented in tabular form for each configuration The data should be taken from the lowest practical speed to maximum in approximately 20 knot increments If the chart method is used it would be prudent to plot the data fair a smooth line thru that data then plot the faired line data to ...

Page 78: ... 60 80 100 120 140 160 180 200 220 240 260 280 300 260 240 220 200 180 160 140 120 100 80 300 280 Zero Error Line Calib data points Sample Flaps UP Gear UP Indicated Airspeed kts or MPH 60 80 100 120 140 140 120 100 80 60 115 Zero Error Line EXAMPLE Enter with 115 kts IAS Exit with 108 kts CAS Flaps and Gear DOWN 108 Calibrated Airspeed kts or MPH ...

Page 79: ...___ 60 80 100 120 140 160 180 200 220 240 260 280 300 260 240 220 200 180 160 140 120 100 80 300 280 Zero Error Line Calibration data for _____________ Flaps UP Gear UP Indicated Airspeed kts or MPH 60 80 100 120 140 140 120 100 80 60 115 Zero Error Line EXAMPLE Enter with 115 kts IAS Exit with 108 kts CAS Flaps and Gear DOWN 108 Calibrated Airspeed kts or MPH ...

Page 80: ...nd when the aircraft fully stalls Sufficient stalls should be conducted to define the repeatability at any one condition and at three or four weights such that a line can be drawn thru the speed points to form a line for cruise and landing configuration Stalls should cover both the cruise configuration and the landing configuration with the gear and flaps in the full down position Intermediate fla...

Page 81: ...ox _____ ft 30 40 140 130 120 110 100 90 80 70 60 50 30 40 140 130 120 110 100 90 80 70 60 50 Reference Line Stall Speed Knots 30 40 140 130 120 110 100 90 80 70 60 50 1700 1800 1900 2000 2100 2200 0 10 20 30 40 50 60 Gross Weight Pounds Angle of Bank Degrees Stall Speed Chart for ___________ ...

Page 82: ...escribed below They should be obtained after the static source the airspeed and the stall speed tests have been accomplished Be sure to make any corrections to your indicated speeds when you define your Vr and V for these tests 65 and 102 KCAS respectively Pick a time when airport traffic is minimal the wind is calm and a brakes release point Coordinate with the tower personnel and obtain the nece...

Page 83: ...itude 0 o C 32 o F Lift off 50 ft Ground Roll Clear 50 ft 1800 65 75 SL 2000 4000 6000 2000 65 75 SL 2000 4000 6000 2200 65 75 SL 2000 4000 6000 Weight LBS Takeoff Speed KCAS Pressure Altitude 20 o C 68 o F Lift off 50 ft Ground Roll Clear 50 ft 1800 65 75 SL 2000 4000 6000 2000 65 75 SL 2000 4000 6000 2200 65 75 SL 2000 4000 6000 Weight LBS Takeoff Speed KCAS Pressure Altitude 40 o C 104 o F Lift...

Page 84: ...at higher altitudes climb at 150 kts IAS with flaps and gear up This data can be obtained during normal cross coun try flights with a little preplanning to record the data It is suggested that data of OAT rate of climb and gross weight be recorded whenever possible then when sufficient data has been generated over a temperature and weight range the data can be added to the chart below ASSOCIATED C...

Page 85: ...TS Several other charts of a general nature are included for your use The aforemen tioned Part Throttle Fuel Consumption chart for one common engine is shown If this is not your engine your engine s manual will have a similar chart and it is recommended that you include such a chart photo reduced to fit in your POH Achart of the International StandardAtmosphere as well as a Fahrenheit to Celsius c...

Page 86: ...V 16 February 2008 Legacy 100 120 140 160 180 200 220 240 260 SL 4 000 8 000 12 000 True Airspeed Knots Cruise Speeds Sample Pressure Altitude Feet Sample Cruise Speed Data 75 65 55 ...

Page 87: ...V 17 February 2008 Legacy 100 120 140 160 180 200 220 240 260 SL 4 000 8 000 12 000 True Airspeed Knots Cruise Speeds Pressure Altitude Feet Cruise Speed Data _______________ 75 65 55 ...

Page 88: ...titude vs Outside Air Temperature Pressure Altitude Feet International Standard Atmosphere ISA 40 SL 2 000 3 000 4 000 1 000 5 000 6 000 7 000 8 000 9 000 10 000 30 20 10 0 10 20 30 50 40 60 ISA 30 C ISA 20 C ISA 10 C ISA 0 C ISA 10 C ISA 20 C ISA 30 C ISA 40 C ...

Page 89: ...V 19 February 2008 Legacy 30 20 10 0 10 20 30 40 50 60 70 80 90 50 40 30 20 10 0 10 20 30 40 50 Fahrenheit to Celsius Conversion 100 110 120 Degrees F Degrees C Temperature Conversion ...

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Page 93: ...GHT AND BALANCE VI 7 COMPUTE THE INDIVIDUAL COMPONENTS WEIGHT AND BALANCE VI 7 COMPLETE THE WEIGHT AND BALANCE FORM VI 8 GENERAL COMMENTS VI 9 SAMPLE CALCULATIONS VI 10 SAMPLE STATION LAYOUT CONTINENTAL IO 550 VI 10 SAMPLE WEIGHT AND BALANCE SHEET IO 550 VI 11 SAMPLE STATION LAYOUT LYCOMING IO 540 VI 12 SAMPLE WEIGHT AND BALANCE SHEET IO 540 VI 13 STATION LAYOUT BLANK VI 14 WEIGHT AND BALANCE BLAN...

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Page 95: ...oper center of gravity is absolutely critical to the safe flight WARNING It is very important that the scales used are accurate Bathroom scales are not considered accurate Flying outside the approved center of gravity envelope is dangerous You may need to borrow orrent accurate scales from your local FBO For weight and balance of your Legacy the scales should handle up to 1000 lbs Make sure that y...

Page 96: ...VI 4 February 2008 Legacy FS 0 Leading Edge of Wing BL 27 Measuring Locations Firewall Joggle FS 64 625 Ref Main Gear Nose Tire ...

Page 97: ... to level the aircraft At the same time secure the aircraft so it will not move b Start by establishing the aircraft centerline on the floor Plumb bob off the center of the firewall and then plumb off the center of the fuselage as far aft as possible Connect the marks to form the aircraft centerline c The starting fuselage station reference is the firewall joggle Drop a plumb bob off the left and ...

Page 98: ... taking numbers Keep in mind that if the aircraft is not upholstered or painted all these numbers will change We suggest that for records you record the weight on each main gear separately a Weigh the aircraft empty To accurately weigh the aircraft empty all fuel should be drained from the wings and the engine should contain a normal amount of oil b Repeat measurements with a pilot c Repeat measur...

Page 99: ...r 515 x 50 125 25814 375 Main Gear 958 x 104 25 99871 5 Total 1473 125685 875 Empty weight 1473 lbs C G FS 85 32 Step 4 Compute the individual Components Weight and Balance In step two you weighed the aircraft under several different conditions with pilot then with fuel etc This will be used to determine the center of gravity for these individual items To get the individual moment arms use the fol...

Page 100: ...ilot is 206 lbs needed for calculation Total moment weight 498 lbs x 50 125 1181 lbs x 104 25 148 081 5 inch lbs Moment arm 148 081 5 125 685 88 206 108 72 inches In explanation the center of gravity of the pilot is at FS 108 72 Repeat this calculation to determine fuel If you would like you can also do it for the baggage compartment or you can use the number provided for the center of the baggage...

Page 101: ...so be familiar with the effect of aircraft weight A higher aircraft weight decreases aircraft performance and raises the stall speed The entire flight envelope should be explored by the pilot to become familiar with the aircraft We stress that aft C G and higher weights should be experimented with very cautiously The minimum altitude for practicing stalls in the Lancair Legacy is 5 000 feet Unders...

Page 102: ... S 6 4 6 2 5 R e f FS 0 WEIGHT AND BALANCE SHEET E X A M P L E C o n t i n e n t a l I O 5 5 0 N o s e G e a r F S 5 0 F u e l F S 1 0 0 4 5 M a i n G e a r F S 1 0 4 6 2 5 P i l o t s F S 1 0 8 7 1 B a g g a g e F S 1 4 1 C G FS 87 8 to FS93 81 10 to 25 MAC ...

Page 103: ...em Weight Arm Moment lbs inches lb inches Empty Aircraft 1553 87 94 136470 82 Fuel 360 100 45 36162 Pilot 200 108 72 200 Co Pilot 0 108 72 0 Baggage 50 141 7050 Total Weight 2163 Total Moment 201526 82 C G Total moment Total Weight 93 17 MAC 21 38 Percent MAC C G Leading Edge of MAC 40 16 x 100 ...

Page 104: ...e F S 6 4 6 2 5 R e f WEIGHT AND BALANCE SHEET CG FS 87 8 to FS 93 72 10 to 25 MAC E X A M P L E L y c o m i n g I O 5 4 0 N o s e G e a r F S 5 0 1 2 5 F u e l F S 1 0 0 4 5 M a i n G e a r F S 1 0 4 2 5 P i l o t s F S 1 0 8 7 1 B a g g a g e F S 1 4 1 ...

Page 105: ...ght Arm Moment lbs inches lb inches Empty Aircraft 1473 85 32 125685 88 Fuel 210 100 45 21094 5 Pilot 180 108 72 19568 99 Co Pilot 180 108 72 19568 99 Baggage 50 141 7050 Total Weight 2093 Total Moment 192968 36 C G Total moment Total Weight 92 19 MAC 21 2 Percent MAC C G Leading Edge of MAC 40 16 x 100 ...

Page 106: ... l l J o g g l e F S 6 4 6 2 5 R e f WEIGHT AND BALANCE SHEET N o s e G e a r F S _ _ _ F u e l F S _ _ _ _ _ _ _ M a i n G e a r F S _ _ _ _ _ _ P i l o t s F S _ _ _ _ _ _ _ B a g g a g e F S _ _ _ _ C G FS ____to___FS _____ 10 to 25 MAC ...

Page 107: ..._________ Owner __________________________ Item Weight Arm Moment lbs inches lb inches Empty Aircraft Fuel Pilot Co Pilot Baggage Total Weight Total Moment C G Total moment Total Weight ______ MAC ______ Percent MAC C G Leading Edge of MAC 40 16 x 100 ...

Page 108: ...VI 16 February 2008 Legacy NOTES ...

Page 109: ... AND EXITS VII 10 CONTROL LOCKS VII 10 ENGINES VII 10 GENERAL INFORMATION VII 10 ENGINE CONTROLS VII 11 ENGINE INSTRUMENTATION VII 11 ENGINE STARTING VII 13 ACCESSORIES VII 14 FIRE DETECTION EXTINGUISHING VII 14 ABNORMAL OPERATION VII 15 PROPELLERS VII 15 FUEL SYSTEM VII 15 HYDRAULIC SYSTEM VII 17 BRAKE SYSTEM VII 19 ELECTRICAL SYSTEM VII 19 FLAP ELECTRICAL SYSTEM VII 21 AIRCRAFT LIGHTING VII 22 H...

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Page 111: ... to the construction manual for detailed systems descriptions The construction manual also serves as a parts reference AIRFRAME Your Lancair is constructed of the highest aircraft quality materials Accordingly your construction techniques should match that quality Following the assembly manual should cover most if not all your questions concerning the various tech niques involved Materials The Lan...

Page 112: ...own Radio Stack Rheostats ELT Circuit Breakers Trim Controls Emergency Smoke Hood Emergency Gear Dump Valve Throttle Prop Mix Fresh Air Valve Fuel Selector Valve Trim Systems It is essential that you familiarize yourself with the cockpit before flight Each cockpit may be slightly different Emergency Smoke Hook ...

Page 113: ...As you build time in your aircraft you will become familiar with the trim tab positions for the different configurations It is essential that all trims are set in the correct positions prior to takeoff Both the rudder and elevator trims have position indicators however for roll you can determine approximate position by looking at it GROUND CONTROL The Lancair is controlled on the ground using diff...

Page 114: ...stablishing approach flaps is to time the application of the down flap power Full up and full down are determined by the setting of microswitches which deactivate the motor Power for the flap motor comes from the primary electrical buss A flap electrical schematic is shown on the next page Control Switch To Ground Buss To Positive buss thrug 5A fuse or Circuit Breaker Flap Motor with Limit Switch ...

Page 115: ...as it retracts into the nose gear well Gear Operations In the fully extended position the gear linkage is over centered In its retracted position the gear is held up by system pressure Retracting the gear is accomplished by activating the gear up switch This initiates the pressure buildup to 1200 psig by the hydraulic pump unlocks the over center links and raises the gear Each gear has its own hyd...

Page 116: ...ed down by the pressure in the gas strut and the main gears by their weight A typical dump valve is shown below and is located under the instrument panel on the left side of the center console by the pilot s right knee NOTE This valve is located by the pilot s right knee Its operation should be checked periodically NOTE Following use of the dump valve some yawing of the aircraft may be required to...

Page 117: ...air could encounter unexpected clear air or wake turbulence or require an evasive maneuver which could change loose baggage into control jamming debris and become a hazard to the flight anywhere from a nuisance to being catastrophic ANTICIPATE THE LIKELIHOOD OF NEGATIVE G FLIGHT CONDITIONS FOR EVERY FLIGHT SEATS BELTS SHOULDER HARNESS Your Legacy is fitted with seat belts and shoulder harnesses Th...

Page 118: ...ecommend that you use some sort of rudder gust lock And while we would all like to have a hangar for our machine those of us who are not so lucky may have to resort to some additional protection for severe weather This can be provided by battens for the ailerons elevators and rudder These battens are simply padded pairs of board such as 3 by 4 by 3 8 They can be slipped over and under control surf...

Page 119: ...on running the engine dry of fuel All engines utilize a throttle to control the amount of airflow into the engine re stricting it with a butterfly throttle valve in the intake system Full throttle allows unrestricted airflow into the engine resulting in manifold pressures up to ambient or even greater if you have some form of ram air pressure recovery system resulting in maximum power output Contr...

Page 120: ...r near its peak exhaust temperature means that you are operating at the near optimum fuel air ratio Exhaust gas temperature is kept within limits indirectly by establishing the proper mixture for that power setting Adirect measurement of EGT is common and many devices are available in this regard Some measure only the hottest cylinder others measure all six Some measure both EGT and cylinder head ...

Page 121: ... due to the fuel vaporization at the throttle valve These installations however generally have an equivalent valve termed alternate air This also utilizes an alternate source of air for the intake system which is somewhat warmed but is pri marily for protection from the formation of ice on the intake air inlet screen filter or passageways This valve may be spring loaded such that it opens automati...

Page 122: ...intains This should generally be between 4 8 and 5 2 inches of mercury For IFR flying a small gauge is available for monitoring this vacuum and is highly recommended Vacuum pump failures like many others occur at just the wrong time and are often insidious as the gyro may just slowly wind down to become useless Fire Detection Extinguishing Built in fire detection is not provided nor is an extingui...

Page 123: ...tenance and vastly increased reliability No small reward PROPELLERS Your Lancair may be fitted with several different propeller engine combinations Care of any propeller is vitally important as it is a very highly stressed component Loss of even a portion of a blade can be catastrophic in flight Nicks and scratches cause stress risers and cannot be neglected The repaired contour of any repair shou...

Page 124: ...nt with check valve Fuel Passage Dry Bay Gas cap Two different styles are available through KCI One is a plastic cap SPRL KCI and the other is a locking metal cap Fuel vent upper Fuel passage lower Fuel Pump Fuel Selector Valve Fuel drains Flexible fuel supply line Slosh doors in rib Flexible fuel return line Continental Engines To engine ...

Page 125: ...DRAULIC SYSTEM A self contained hydraulic system is used to operate the landing gear The pump is electrically powered When the gear up position is selected the pump is activated and 1200 psi is provided to the up side of a piston operating the mechanism raising the gear and in turn operating the gear doors This pressure is maintained although the electric pump is disabled by an up limit pressure s...

Page 126: ...l gas strut will drive the nose wheel down This gear dump valve is located left side by the pilot s right knee Note This valve is located by the pilot s right knee Its operation should be checked periodically Original Hydraulic Power Pack Installation Fig 2 Produce a lightening hole Also serves as an access hole should it be required Battery box Power grid 1 x 3 x 3 1 8 phenolic spacer blocks A C ...

Page 127: ...depress each pedal to verify a firm pedal Your initial flights in the Lancair like any new aircraft will require extra caution until you become familiar with the aircraft A brake reservoir is located on the firewall The brake system should be bled on a regular basis to ensure a sufficient amount of fluid ELECTRICAL SYSTEM The Lancair basic electrical system consists of an alternator a voltage regu...

Page 128: ...e pressure is achieved L Mag R Mag Starter Engine Noise suppressor Aircraft Spruce 11 08060 Battery Starter Relay A Master Relay F1 F2 Shielded wire Shielded wire Cockpit ground post Avionics Master Ammeter Primary Master bus B S R L Ignition switch Master switch Ref Firewall Fuses 5 Amp Fuses Amp Avionics bus Terminal block Fuses 50 Amp Alternator B Shunt Voltage Regulator See Mfg schematic for s...

Page 129: ...ted behind the pilot s seat Attached to the actuator shaft is the limit switch assembly with the full up and down limit switches These determine the extreme flap positions Partial flaps are obtained by simply timing the actuation of the Green Gear Lights Gear Nose Gear Right Micro Switch Gear Left 22 22 22 To Buss Bar To Buss Bar 22 10 Green 10 Blue 2 Low Pressure Switch Gear Switch 1 Gear Down Re...

Page 130: ...he main buss have an approximately sized circuit breaker have their own switch or rheostat and as was indicated earlier their own ground return wire required by the composite material of the Lancair The avionics are operated off a separately powered avionics buss to allow the whole set of equipment to be turned off and on at one time Their lighting systems are integral and with this configuration ...

Page 131: ... the warm air plumbing is equipped with this arrangement Ventilation is obtained from two flush mounted air intake scoops which direct the outside air into the cockpit one on each side wall During ground operation the canopy can be left partially open until takeoff The canopy can never be opened in flight the latches must remain locked PITOT STATIC SYSTEM An electrically heated pitot tube is stand...

Page 132: ...VII 24 February 2008 Legacy Pitot Static System VSI ALT A S Static Port Left Side Static Port Right Side Heating Element Airspeed Pressure Switch ENCODER ...

Page 133: ...ked outside VACUUM SYSTEM The vacuum system is powered by a vacuum pump driven by the engine Its opera tion is vital to many gyro instruments and is indicated by a pressure gauge The gauge can be one which indicates the pressure value or a small indicator with a red or green flag Either is acceptable however the gauge may provide an indication of gradually decreasing pump capability and thus provi...

Page 134: ...VII 26 February 2008 Legacy NOTES ...

Page 135: ...VII 27 February 2008 Legacy NOTES ...

Page 136: ...VII 28 February 2008 Legacy NOTES ...

Page 137: ...ND HANDLING VIII 6 MAIN WHEEL JACKING VIII 7 NOSE WHEEL JACKING VIII 8 OUT OF SERVICE CARE VIII 8 PREPARATION FOR SERVICE VIII 9 FUEL SERVICING VIII 9 OIL SYSTEM SERVICING VIII 9 BATTERY VIII 10 TIRES VIII 11 LANDING GEAR SHOCK ABSORBERS VIII 11 BRAKES VIII 12 INDUCTION AIR FILTER VIII 12 INSTRUMENT VACUUM SYSTEM VIII 12 PROPELLER VIII 12 ELECTRICAL POWER VIII 13 CARE AND CLEANING VIII 13 ENGINE V...

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Page 139: ...aircraft throughout its life This obviously has many advantages and is probably part of the reason you purchased the aircraft 51 Documentation Requirements As you build your aircraft it is important that you keep a good record of your construction Keeping a record of all the parts purchased is important as well as a photo album Pictures of you in the process of building are considered mandatory by...

Page 140: ...ircraft and owner pilot maintenance is significantly restricted It is then treated just as a commercially built aircraft except that an AI is not required for annuals and A P can perform annuals on an amateur built aircraft The origi nal builder still may perform any and all work on your aircraft the one he built however For aircraft registered in the United States FAR Part 43 defines the types of...

Page 141: ...ub bing areas etc The 100 hour inspection takes a more in depth look at the aircraft for structural cracks delaminations etc much as an annual inspection It is recommended that the aircraft be thoroughly washed the engine cleaned compression checked and a complete review of the aircraft and engine log book be made to insure all FAA or appropriate registering agency requirements for such items as a...

Page 142: ...ile ground handling your Lancair the propeller should be placed in the horizontal position Use care when turning the propeller ASSUMETHE MAGNETOS ARE HOT Towing Your Lancair is an exceptionally light aircraft and should present no problems while ground handling Mechanically attached towing is generally not recommended If mechanical towing is necessary a tow bar fitting in the nose wheel axle shoul...

Page 143: ...r any rope shrinkage Manila or hemp ropes should not be used Chains can be essentially snug Chocks for the main gear wheels are also recommended MAIN WHEEL JACKING As of today Lancair does not have a recommended hardpoints for jacks for the Legacy However the following method works well Place underneath main spar as far inboard as possible Padding LIV jack pad available from KCI Tall Jack 10 x 10 ...

Page 144: ...he elements is the primary concern With the Lancair it may be easiest to remove the wings and store in your garage where you have or can provide some control over temperature and humidity In any case the most susceptible element of your aircraft is the engine s cylinder walls and bearing surfaces The engine should be preserved according to the manufacturer s directions The airframe will withstand ...

Page 145: ...ced battery Install spark plugs and check the oil level The oil used for storage should be removed and proper oil installed The fuel tanks should be checked for water accumulation and purged as required Following a short but thorough engine ground check the aircraft should be flown for 30 minutes maximum and given a very thorough post flight inspection FUEL SERVICING The Lancair fuel requirements ...

Page 146: ...rom more frequent changes to the installation of an improved filter system Metallic particles may vary from aluminum to steel to stainless steel Following the initial break in period during which some metallic particles are normal almost any amount there after becomes cause for concern If subsequent changes show additional metallic particles the source should be determined The type can be somewhat...

Page 147: ...o the wheel well and may damage the mechanism and the aircraft structure LANDING GEAR SHOCK ABSORBERS Visually inspect the oleo struts for any signs of leakage A leak may also be in ternal in the strut so also inspect the bottom of shaft for any residue through the hole of the fork The struts contain air nitrogen and oil and are a sealed system The nose wheel strut contains a shimmy dampening syst...

Page 148: ...hould be a minimum of 0 150 inches thick The brake pucks should be replaced when less than this value INDUCTION AIR FILTER Operation of the aircraft in dusty areas requires that a filter be installed and changed periodically to preclude premature engine degradation Removal of the filter requires removal of the cowling and should be accomplished at least on an annual basis If operating in dusty are...

Page 149: ...Aviation use a remotely mounted voltage regulator Its d c voltage output should be the same i e 14 2 to 14 8 volts An alternator should never be operated open circuit that is without a load The Lancair uses a negative ground system Filters in the system reduce noise in the avionics from the alternator and the magnetos Excessively high voltage regulation will cause overcharging of the battery and s...

Page 150: ... if there is any question as to the compatibility of the cleaner and the upholstery or carpet materials If acceptable clean areas of spots as necessary Detergent foams can be used to clean carpets if used per the manufacturer s instructions Interior plastic parts should be cleaned with a water damp cloth Oil and grease can be removed with cloth dampened slightly with kerosene Volatile solvents suc...

Page 151: ...ancairs ENGINE Clean the engine with a neutral solvent While the engine is warm but not hot spray with the solvent and allow to set a few minutes Follow with a spray wash and allow to dry Avoid excessively high pressures which can force entry of wa ter and or solvents under seals resulting in contamination of the sealed system or entry thru the firewall into the cabin Use caution and protect any e...

Page 152: ...ss dispersant oil Change oil filter Change fuel filters Check battery fluid Check brake lines Check all gear doors nose main gears Check wing bolt torque Control surface hinges Change oil and filter Clean or change engine air filter Lube landing gear mechanism Check control surface hinges INTERVAL Preflight First 25 hrs First 50 Hrs ...

Page 153: ... 1700 RPM 7 Cycle prop check prop governor operation 8 Suction_______ Inches of Hg 4 6 normal 9 Alternator output check for normal 10 Full power manifold pressure______ Hg ______RPM 11 Check for general running conditions vibrations 12 Check idle speed mixture________rise _____ RPM 13 Magneto ground check 14 Compression check 1 80 2 80 3 80 4 80 5 80 6 80 15 Drain engine oil 16 Remove oil filter o...

Page 154: ... governor for leaks security condition of cable end 35 Check starter for security condition 36 Check alternator mount for security condition of wiring and belt for condition and tension 37 Check vacuum pump for security condition 38 Check tach cable or wiring for security condition 39 Wash engine CAUTION DO NOT CONTAMINATE VACUUM PUMP or INDUC TION SYSTEM WITH FLUID 40 Lubricate engine controls an...

Page 155: ...k condition of instrument panel wire hoses vacuum filters 15 Check compass for fluid level correction card 16 Check instrument lights 17 Check instruments for proper markings general condition security 18 Clean inside of cabin insure that drain holes are clea 19 Inspect fuel lines tank for security leaks 20 Inspect pitot static lines WING 1 Remove inspection covers 2 Inspection lubricate all bell ...

Page 156: ...for general condition cracks 5 Check tires for wear condition proper inflation 6 Check wheel bearings for corrosion wear Repack w grease 7 Check main gear trailing beams bolts for wear 8 Check main gear weldment for fore aft end play 9 Check compression assemblies bolts for wear disassembly required 10 Check nose gear drag link at the knee for wear or hole elongation disassembly re quired 11 Check...

Page 157: ... covers 2 Inspect rudder hinges rudder attachment pin safetied 3 Inspect trim tabs elevator hinges lubricate GENERAL 1 Check all optional equipment for security proper operation 2 Check all placards 3 Check composites for signs of delaminations distortion cracks damage lost paint or other evidence of failure 4 Run up engine check oil pressure all gauges for proper operation 5 Magneto check 1700 RP...

Page 158: ...VIII 22 February 2008 Legacy NOTES ...

Page 159: ...X 4 PAGE NUMBERING IX 4 STRUCTURE OF SUPPLEMENTS IX 4 YOUR SUPPLEMENTS IX 5 LOG OF SUPPLEMENTS IX 6 SUPPLEMENT FOR THE SYSTEM OR EQUIPMENT IX 7 GENERAL DESCRIPTION PURPOSE OF EQUIPMENT IX 7 LIMITATIONS IX 7 EMERGENCY PROCEDURES IX 10 NORMAL PROCEDURES IX 14 PERFORMANCE IX 16 SYSTEM DESCRIPTION IX 16 SERVICING AND MAINTENANCE IX 17 NOTES IX 18 ...

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Page 161: ...hen equipped with the various optional systems and equipment not provided with the standard airplane This section in your Handbook is intended to cover the systems or specific pieces of equipment you have installed in your Lancair When a system or piece of equipment is installed a Supplement should be installed in your Pilot s Operating Handbook for reference at all times While we will identify th...

Page 162: ...cutive num bering system such as 1 of 3 2 of 3 or 1 6 2 6 etc STRUCTURE OF SUPPLEMENTS Once again quoting the GAMA specification Each supplement shall be a self contained miniature Pilots Operating Handbook as a minimum and be included in the Pilots Operating Handbook at all times Section 1 General Information This should identify the purpose of the system or equipment and who has approved the sys...

Page 163: ... change so state YOUR SUPPLEMENTS The intent of the preceding tutorial is to provide you with sufficient guidelines to create your own specific supplements if as required The result should provide you with a Pilots Operating Handbook equal to the best Since it is your book for your airplane it deserves no less The various blank forms on the next pages will assist you in formatting your own supplem...

Page 164: ...Operating Handbook and Airplane Flight Manual for Lancair Model ____________ N_____________ Log of Supplements Supplements must be in the airplane for flight operations when subject equipment is installed Part Number Subject Rev No Date ...

Page 165: ...IX 7 February 2008 Legacy Supplement for the System or equipment General Description purpose of equipment Limitations Of equipment Approved by _______________________ Date ______________________________ ...

Page 166: ...153 169 18 4 9 13 3 7 9 2400 137 152 19 2 8 14 7 8 2300 134 148 19 8 500 10 22 7 14 2 2400 192 220 15 5 10 22 7 13 6 2300 190 217 15 9 EGT Peaked 10 19 6 12 2400 177 203 16 at 1 440 9 20 11 5 2300 176 202 16 9 8 16 2 10 1 2400 158 181 17 9 9 16 9 9 8 2300 155 178 18 2 8 14 8 5 2400 142 163 19 2 8 14 3 8 3 2300 143 164 19 8 8 15 8 2 2200 143 164 20 8 15 3 8 1 2100 143 164 20 2 8 16 8 2000 143 164 2...

Page 167: ... 6 11 5 2400 165 208 18 1 0 17 9 11 2300 163 206 18 7 1 15 2 9 4 2400 146 185 19 7 EGT Peaked 2 15 2 9 3 2300 146 185 19 9 at 1 392 2 13 1 8 2 2400 135 171 20 9 3 13 5 8 2300 134 170 21 2 15 500 4 17 2 10 8 2400 160 208 19 2 3 14 3 8 4 2400 142 185 21 8 2 13 3 7 9 2400 135 176 22 3 16 500 2 16 5 10 2 2400 155 205 20 1 2 15 2 9 2400 146 193 21 4 2 13 8 8 1 2400 137 182 22 5 2 12 8 7 5 2400 130 173 ...

Page 168: ...IX 10 February 2008 Legacy Emergency Procedures ...

Page 169: ...IX 11 February 2008 Legacy Emergency Procedures ...

Page 170: ...IX 12 February 2008 Legacy Emergency Procedures ...

Page 171: ...IX 13 February 2008 Legacy Emergency Procedures Continued ...

Page 172: ...IX 14 February 2008 Legacy Normal Procedures ...

Page 173: ...IX 15 February 2008 Legacy Normal Procedures Continued ...

Page 174: ...IX 16 February 2008 Legacy Performance System Description ...

Page 175: ...IX 17 February 2008 Legacy Servicing and Maintenance Approved by ___________________ Date __________________________ ...

Page 176: ...IX 18 February 2008 Legacy NOTES ...

Page 177: ...RCES OF INFORMATION X 5 AIRMAN S INFORMATION MANUAL X 5 ADVISORY INFORMATION X 6 FAAADVISORY CIRCULARS X 6 GENERAL FLIGHT TOPICS X 7 FLIGHT PLANS X 7 MOUNTAIN FLYING X 7 SEVERE WEATHER X 8 ICING X 8 MARGINAL VFR FLIGHT X 9 NIGHT FLYING X 9 VERTIGO HYPOXIA X 9 ENGINE FAILURES X 10 AEROBATICS X 12 HAPPY FLYING KEEP IT SAFE ...

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Page 179: ...he machine from someone else that same information can prove invaluable This particular section however can be of benefit to all of us As the old adage goes we re never too old to learn Much of this will undoubtedly be a refresher and some suggestions may not be exactly to your preference That does not mean either is wrong as for example cross wind landings can be made from eigher a crab or slip a...

Page 180: ...ogged but how well those hours are flown how aware we are during those hours how we understand the differences of this flight from the last one Making each flight a learning experi ence will gather that precious experience much quicker First Flight Prior to your first flight in your Lancair it is only prudent that you obtain some training in type You are encouraged to take advantage of this type o...

Page 181: ... to two minutes or more AVOID THEM SOURCES OF INFORMATION There are numerous sources of information available to make your flying not only safer but more enjoyable as well Of course the number one source is our FAA or your country s regulating authority F A R Part 91 covers the General Operating and Flight Rules for the U S This document covers subjects such as the responsibilities of the pilot us...

Page 182: ... sale as well as those distributed free of charge by the FAA as well as ordering information Some of the free circulars are 00 24 Thunderstorms 00 50 Low Level Wind Shear 20 5D Plane Sense 20 93 Flutter Due to Ice or Foreign Substance on or in Aircraft Control Sur faces 20 105 Engine Power Loss Accident Prevention 43 12 Preventative Maintenance 60 4 Pilot s Spacial Disorientation 60 9 Induction Ic...

Page 183: ...nsportation compared to ground means and can be done safely but is not without its special concerns Operation of the aircraft is generally at much higher altitudes where engine performance is poorer and stall speeds are higher due to the less dense air Care must be taken to allow for these effects by reducing the gross weight if necessary More room must be allowed for takeoff and landings and slow...

Page 184: ...ics Should you begin to accumulate ice in flight as soon as you notice it attempt to avoid by changing altitude or reversing course Remember that preflight briefing where you noted the potential for icing and determined what your out would be If that ice does not sublimate evaporate as ice or melt prior to your land ing increase your approach speed and land hot If circumstances permit make an oppo...

Page 185: ...ear nights dead reckoning navigation from lights to lights is easier due to generally clearer air With a well equipped and operating aircraft acceptable terrain enroute and predictable sur face winds just in the case of engine failure night flights have their own special reward Vertigo Hypoxia Vertigo is the condition where your inner ear based on gravity gives you that sense of which way is up Sm...

Page 186: ...e realization of the symptoms evaluate the potential cause and take the appropriate action Recovery from hypoxia is dependent upon obtaining oxygen lower altitude Hyperventilation requires a few seconds for the blood balance to be restored Both of these problems are aggravated by smoking and alcohol which also upset the bloods ability to carry oxygen to the brain Avoid them for your safety and tha...

Page 187: ...equipped with carburetors as opposed to a fuel injection system Moist air at temperatures of 40 to 70 F are ideal conditions for carburetor icing Be aware and you and your carburetor can live happily ever after Water in the fuel system is another cause of engine failure In cold weather it can freeze in the filter tank or lines and limit or totally restrict fuel flow to the engine Preflight checks ...

Page 188: ...ing aerobatic maneuvers Aerobatics are essentially single seat with no other weight in the fuselage Improperly flown maneuvers can result in reaching a stalled condition and a yaw at the same time the recipe for a spin The Lancair has demonstrated its ability to recover from spins at both forward and aft CGs with the standard recovery technique i e opposite rudder stick forward to unstall the wing...

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