Lancair ES-P Pilot Operating Handbook Download Page 89 | Manualshive

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down on the fuselage just forward of the empennage.

(2) Spin the nose wheel. It should spin over one or two turns at

the most. If excessive rotation occurs the axle nut must be
retightened and the test conducted again until satisfactory.
Verify that the bearings are properly snug; there must be no
free play between bearings and race. Check that the side
bushings are properly snugged against bearings and that they
are not worn. The shimmy damper system should provide 20
to 50 ft-lbs of drag when the wheel/strut is moved (rotated left
and right about the strut axis) at a moderate rate. Fast rotation
rates should create higher torques.

BRAKES

The brakes are independent systems on each of the main gear wheels.
The single fluid reservoir is located on the top left side of the firewall.
The toe brakes should depress approximately 1/2 inch before any
pressure is generated on the brake when properly serviced. The brake
pucks should be at least 0.150 inches thick and should be replaced
when less than this value.

PROPELLER

The propeller should be serviced according to MT’s instructions. It is
a highly stressed component and any failure has the potential of being
catastrophic. Treat it with care. The MT propeller is sensitive to
leading edge damage and possible erosion shield delamination. Refer to
their service bulletins for tolerances and repairs.

WARNING

Use care when handling the propeller. Ensure the
magnetos are OFF, the throttle CLOSED and the
mixture in the CUT-OFF position. Then remain
as clear as possible during the dressing operation.
Be prepared for a cylinder to fire when moving
the propeller to a new position.

ELECTRICAL POWER

This aircraft has a 24-volt dual alternator / dual bus negative ground
electrical system. Both busses diode feed an essential bus containing
flight critical components. Fuses protect most items, with some critical
elements protected by circuit breakers mounted on the instrument
panel.

Two alternators produce alternating current, which is then converted by

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Summary of Contents for ES-P

Page 1: ...BOOK AND AIRPLANE FLIGHT MANUAL ES P Manufacturer Heizer IJ Serial No 001 Model ESP Lancair Kit No 120 This aircraft is FAA Approved in the EXPERIMENTAL category based on FAR 23 This document must be carried in the aircraft ...

Page 2: ... Woodinville Washington 98072 WARNING This is an experimental aircraft having experimental documentation No aspect of this documentation can be assumed correct The pilot must accept all risk and responsibility associated with being anywhere near this airplane do not fly in this aircraft if you do not personally agree and accept all responsibility ...

Page 3: ...rning symbol means that information which follows is of critical importance and concerns procedures and techniques which could cause or result in personal injury or death if not carefully followed CAUTION The use of a Caution symbol means that information which follows is of significant importance and concerns procedures and techniques which could cause or result in damage to the airplane and or i...

Page 4: ...ION 3 LIMITATIONS SECTION 4 EMERGENCY PROCEDURES SECTION 5 NORMAL PROCEDURES SECTION 6 WEIGHT BALANCE SECTION 7 SYSTEMS DESCRIPTIONS SECTION 8 HANDLING SERVICING MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 SAFETY INFORMATION SECTION 11 ADDENDUM ...

Page 5: ...MPORTANT NOTICE 2 DESCRIPTIVE DATA 4 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 7 METEOROLOGICAL TERMINOLOGY 8 POWER TERMINOLOGY 9 ENGINE CONTROLS INSTRUMENTS 9 PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 10 WEIGHT AND BALANCE TERMINOLOGY 11 ...

Page 6: ...airplane Again the operator should be familiar with the Federal Aviation Regulations as applicable to the operation and maintenance of experimental airplane and FAR Part 91 General Operating and Flight Rules The aircraft must be operated and maintained in accordance with any FAA Airworthiness Directives that may be issued against it It is also prudent and mandatory to operate within any establishe...

Page 7: ...ments direct from Lancair for appropriate placards limitations normal emergency and other operational procedures for proper operation of their Lancair with any optional equipment installed WARNING When this handbook is used for airplane operational purposes it is the pilot s responsibility to maintain it in current status ...

Page 8: ...r 100LL Minimum grade Aviation Gasoline conforming to ASTM D0 76 MLG 5572 latest revision SYSTEMS CAPACITIES Fuel capacity 105 US gallons Oil Capacity 12 quarts FILTERS Oil Filter CH48109 1 WEIGHTS Empty weight 2480 lbs Max gross take off 3600 lbs Max landing weight 3550 lbs Max weight in baggage compartment 175 lbs CABIN DIMENSIONS Length 74 inches Height max 47 inches Width Front seat 45 inches ...

Page 9: ...SPECIFIC LOADING max take off weight Wing area 140 ft2 Wing loading 25 7 lb ft2 Power loading 350 HP 10 3 lb h p ...

Page 10: ...Basic Airframe Dimensions ...

Page 11: ...f an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not over stress the airplane VFE Maximum Flap Extend Speed is the highest speed permissible with wing flaps in a prescribed extended position VN Maximum Level Speed at full power V...

Page 12: ...s 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 outside air temperature is 56 5ºC 69 7ºF is 0 00198 C 0 003566ºF per foot and zero above that altitude OAT Outside Air Temperature The free air static temperature obtained either from inflight temperature indicators adjusted for instrument er...

Page 13: ...o be understood as the headwind or tailwind components of the reported winds POWER TERMINOLOGY Takeoff Maximum Continuous The highest power rating not limited by time Cruise Climb The power recommended for cruise climb ENGINE CONTROLS INSTRUMENTS Throttle Control Used to control power by introducing fuel air mixture into the intake passages of the engine Settings are reflected by readings on the m...

Page 14: ... of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval Demonstrated Crosswind Velocity The demonstrated 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 handbook is t...

Page 15: ...G The point at which an airplane would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane CG Arm The arm obtained by adding the airplane s individual moments and dividing the sum by the total weight CG Limits The extreme center of gravity locations within which the airplane must be operated at a given weight Usable F...

Page 16: ...taxi and run up fuel Maximum Take Off Weight Maximum weight approved for the start of the take off run Maximum Landing Weight Maximum weight approved for the landing touchdown Zero Fuel Weight Weight exclusive of usable fuel Tare The weight of chocks blocks stand etc used on the scales when weighing an airplane Jack Points Points on the airplane identified by the manufacturer as suitable for suppo...

Page 17: ...PERATING LIMITATIONS 3 OIL SPECIFICATION 4 POWERPLANT INSTRUMENT MARKINGS 4 MAXIMUM WEIGHTS LBS 4 CENTER OF GRAVITY LIMITS 4 FLIGHT LOAD FACTOR LIMITS 5 KINDS OF OPERATION LIMITS AND PILOT REQUIREMENTS 5 ICING CONDITIONS 5 COMMERCIAL OPERATIONS 5 FUEL MANAGEMENT 5 SEATING CAPACITY 5 WINTER OPERATIONS 5 ...

Page 18: ... 220 163 FL250 Normal Operating Range Green Arc 67 174 Maneuvering Speed Decrease 3 knots for each 1000 ft above 1200 feet pressure altitude VA 135 2600 lbs 96 2600 FL250 158 3600 lbs 119 3600 FL250 Max Structrual Cruising Speed Decrease 3 5 knots for each 1000 above 12 000 pressure altitude VNO 174 Full Flap Operating Range White Arc 56 122 Maximum Flap Extended Speed Decrease 2 4 knots for each ...

Page 19: ...ct any degradation due to age or number and quality of overhauls Rated max continuous BHP 350 HP 2700 RPM Recommended Max cruising BHP 262 HP 2500 RPM Max continuous manifold pressure 38 5 Hg Cylinder Head Temperatures F Normal flight operation max temperature 420 F Maximum allowable 460 F Turbine Inlet Temperature F Maximum allowable 1750 1850 for 30 sec Oil Temperatures F Maximum 240 Minimum for...

Page 20: ...ed line 240 OIL PRESSURE PSI Minimum Idle Red line 10 Caution Range Yellow region 10 30 Operating Range Green region 30 60 Maximum Red Line 100 TACHOMETER RPM Operating Range Green region 600 2700 Maximum Red Line 2700 MANIFOLD PRESSURE IN HG Operating Range Green region 15 38 Maximum Red Radial 38 38 5 FUEL PRESSURE PSIG Operating Range Green region 10 34 Maximum Pressure Red Radial 34 FUEL QUANT...

Page 21: ... VFR and IFR operations with only one pilot The operational minimum equipment and instrumentation for the kinds of operation are detailed in Part 91 of the FARs ICING CONDITIONS Flight into known icing is prohibited COMMERCIAL OPERATIONS Flight operations with passengers for hire are prohibited FUEL MANAGEMENT Do not take off with less than 10 gallons in each tank There is no interconnection betwe...

Page 22: ......

Page 23: ... FLIGHT 8 ENGINE FIRE DURING START 9 EMERGENCY DESCENT 9 MAXIMUM GLIDE CONFIGURATION 9 FORCED LANDING 9 SYSTEMS EMERGENCIES 10 ELECTRICAL SYSTEM PROBLEMS 10 CIRCUIT BREAKERS AND FUSES 10 ELECTRICAL SYSTEM OVERCHARGING 11 ALTERNATOR FAILURE 11 FLIGHT WITH ONE FAILED ELECTRICAL SYSTEM 11 ELECTRIC TRIM AUTOPILOT FAILURE 12 MULTI FUNCTION DISPLAY 13 PRIMARY FLIGHT DISPLAY 13 CARBON MONOXIDE ALERT 13 W...

Page 24: ...ted to capture in a compact format those pilot tasks requiring rapid action The pilot should keep these checklists handy for ready access and he should familiarize him herself with them before flying the aircraft Knowledge of the switches controls gauges etc located quickly even blindfolded is highly desirable Cockpit time prior to ever flying or after an absence is time prudently spent Where more...

Page 25: ...S with flaps up Boost Pump OFF Mixture IDLE CUT OFF Fuel Selector OFF Ignition OFF Flaps LANDING position Master Switches OFF Maintain directional control and make only shallow turns to avoid obstacles ENGINE FAILURE DURING FLIGHT Airspeed BEST GLIDE 100 KIAS with flaps up SpeedBrakes RETRACTED Boost Pump LOW Mixture RICH Fuel Selector SWITCH TANKS Alternate Air OPEN Ignition VERIFY ON NOTE If pow...

Page 26: ...peller is not turning a Oil Pressure Within limits will probably be quite low if oil is cold If no oil pressure indicated engine damage may occur if restart is continued b Throttle Adjust to 15 20 inches manifold pressure until engine temperature reaches operating range Adjust mixture as required c Oil Pressure STABILIZED d Mixture FULL RICH 8 Throttle AS NECESSARY TO PREVENT OVERSPEED Warm up at ...

Page 27: ...ecessary and continue Do not operate the engine in this manner any longer than absolutely necessary The airplane should be landed as soon as practical for engine repairs CAUTION The engine may quit completely when one magneto is switched off if the other magneto is faulty If this happens close throttle to idle and move mixture to idle cutoff before turning magnetos on This will prevent a severe ba...

Page 28: ...t and the choice is made to continue operating the engine proceed as follows NOTE At altitudes above 15 000 feet an over rich mixture may result if the turbocharger fails and the engine may quit operating If this occurs employ the following procedure 1 Mixture IDLE CUTOFF 2 Throttle FULL 3 Propeller CRUISE RPM 4 Throttle CRUISE POSITION 5 Mixture Advance slowly When the proper mixture ratio is rea...

Page 29: ...l Pump AS REQUIRED 8 Mixture ADJUST NOTE If this procedure does not effect a restart descend below 15 000 feet and repeat If the engine still will not start follow the emergency procedures outlined HIGH CYLINDER HEAD TEMPERATURE Mixture ADJUST to proper fuel flow for power Oil Door PUSH to open Airspeed INCREASE If temperature cannot be maintained within limits reduce power land as soon as possibl...

Page 30: ...failure should be anticipated If oil pressure drops without apparent reason from a normal indication of 30 to 60 psi monitor temperature and pressure closely land as soon as possible and have the engine inspected ENGINE FIRE IN FLIGHT Determine if fire is electrical acrid smell if so Master Switches OFF All Electrical Equipment OFF If fire smell clears turn Master switch ON then each item of equip...

Page 31: ...laps UP Propeller PULL to LOWEST RPM SpeedBrakes RETRACTED Airspeed AOA at MAX L D 2 GREEN 100 KIAS Glide distance is approximately 2 0 NM per 1000 feet of altitude loss however this may vary significantly FORCED LANDING When landing site is selected and you are committed to landing off field the following checklist can be completed When assured of reaching the landing site area GLIDE Airspeed BES...

Page 32: ...ges measures the condition of the alternator output while the voltmeter indicates the condition of the airplane s electrical system on a bar graph on the MFD System page The MFD System page shows bus voltage as well as alternator current on bar graphs with a boundary around the group marked electrical CIRCUIT BREAKERS AND FUSES A small number of circuit breakers are located on the instrument panel...

Page 33: ...s the alternator can be recycled by pulling out then pushing in the MAIN ALT or AUX ALT circuit breaker as appropriate If the alternator annunciation message clears the flight can continue normally If the annunciation remains displayed proceed as described in the FLIGHT WITH ONE FAILED ELECTRICAL SYSTEM section FLIGHT WITH ONE FAILED ELECTRICAL SYSTEM The most prudent course of action is probably ...

Page 34: ...ar the L Alt Off or R Alt Off annunciation message and the battery will be in a charging state If the discharging state is not corrected there will be decay in the voltage available to the electrical system of the airplane and systems will cease to operate In the event of total electrical system failure the backup attitude indicator will continue to operate on an internal battery supply for up to ...

Page 35: ...ed by the affected indicator being removed from the display and replaced with a red X Those functions that do not have a red X may still be usable CARBON MONOXIDE ALERT If the carbon monoxide alert activates reset the unit via the G900X soft keys If the unit continues to alert Supplemental Oxygen DEPLOY Land AS SOON AS PRACTICAL Be sure the source of the CO contamination is corrected before furthe...

Page 36: ... the UP deployed position attempt to retract them by cycling to full up then down If all attempts fail to retract them land with them fully extended and use at least 95 KIAS on final UNLATCHED DOOR IN FLIGHT If the door becomes unlatched or opens in flight the first priority is to FLY THE AIRPLANE If the door is still hooked have a passenger hold the handle to prevent further opening If the door h...

Page 37: ...ttempt to check cabin doors for security until cabin is depressurized and airplane is on the ground CRASH AX A crash ax is located under the copilot s seat for use in the event the cabin door cannot be used The blade of the ax points down and the unit is secured with a Velcro strip To use the ax open the Velcro fastener and remove the ax from its sheath It generally works best to strike the corner...

Page 38: ......

Page 39: ...I 9 TAXI 9 BEFORE TAKEOFF Runup 10 TAKEOFF CLIMB 11 NORMAL TAKEOFF 11 MAXIMUM PERFORMANCE TAKEOFF CLIMB 11 NORMAL CLIMB 11 CRUISE 12 LEAN OF PEAK ENGINE OPERATION 12 DESCENT 13 BEFORE LANDING 13 APPROACH 13 APPROACH WITH GLIDESLOPE AND AUTOPILOT 14 APPROACH WITH SPEEDBRAKES DEPLOYED 15 BALKED LANDING Go Around 15 NORMAL LANDING 15 LANDING WITH SPEEDBRAKES DEPLOYED 15 SHORT FIELD LANDING 15 CROSSWI...

Page 40: ...PRESSURIZATION 17 SYSTEM DESCRIPTION 17 PRESSURIZATION CONTROLS 18 OPERATION TAKE OFF CLIMB 19 OPERATION CRUISE DESCENT 20 COLD WEATHER OPERATIONS 20 PREFLIGHT INSPECTIONS 20 ENGINE CONSIDERATIONS 20 CRUISE OPERATION 21 ICING CONDITIONS 21 NOISE 21 ...

Page 41: ...4 71 68 65 31 5 82 79 76 73 70 67 64 31 0 81 78 75 72 69 66 63 30 5 79 76 73 70 67 65 62 30 0 78 75 72 69 66 63 61 29 5 77 74 71 68 65 62 60 29 0 75 73 70 67 64 61 59 28 5 74 71 69 66 63 60 58 28 0 73 70 67 65 62 59 57 27 5 71 69 66 63 61 58 56 27 0 70 68 65 62 60 57 55 26 5 69 66 64 61 59 56 54 26 0 68 65 63 60 58 55 53 25 5 66 64 61 59 56 54 52 25 0 65 63 60 58 55 53 51 LOP Gal Hr 80 19 0 75 17 ...

Page 42: ...n RETRACT Master Switches OFF AUX first then MASTER Fuel Selector Valve FULLEST TANK Oxygen CHECK QUANTITY VALVE ON Oxygen Masks AVAILABLE Door Seal OFF CHECK CONDITION Fire Extinguisher GAUGE GREEN 2 EMPENNAGE Baggage Door LOCKED Static Port CLEAR Tail Tie Down DISCONNECT Control Surfaces CHECK freedom of movement and security Trim Tabs CHECK FOR NEUTRAL POSITION 3 RIGHT WING TRAILING EDGE Flap C...

Page 43: ...l from fuel tank sump quick drain valve to check for water sediment and proper fuel grade Wing Fuel Drain CHECK FOR CONTAMINATION Wheel Fairing CHECK general condition 5 NOSE Propeller and Spinner CHECK for nicks security and oil leaks NOTE Blade shake is allowed up 1 8 inch and a blade angle play of 2o is acceptable Air Inlets CHECK for restrictions or other foreign matter Nose Gear and Tire CHEC...

Page 44: ...el Filler Cap SECURE Pitot Tube CHECK FOR OBSTRUCTIONS Wing Tie Down DISCONNECT Lights CHECK condition and cleanliness Speed Brakes CHECK condition Fuel Tank Vent CLEAR NO OBSTRUCTIONS 7 LEFT WING TRAILING EDGE Aileron CHECK for freedom of movement and security Trim Tab CHECK Attachment security Flap CHECK for movement and security STARTING ENGINE CAUTION Release starter switch as soon as engine f...

Page 45: ...peller Area CLEAR 13 Ignition Switch START release when engine starts 14 Throttle IDLE 900 to 1000 RPM 15 Oil Pressure CHECK 30 to 60 PSI NOTE After starting check for oil pressure indication within 30 seconds in normal temperatures and 60 seconds in cold temperatures If no indication appears shut off engine and investigate STARTING FLOODED ENGINE 1 Mixture Control IDLE Cut off 2 Throttle open 3 M...

Page 46: ...ON 7 Lights ON as required 8 Boost Pump ON FOR 3 TO 5 SECONDS THEN OFF 9 Wait a few seconds Allow all fuel to drain from intake system 10 Mixture RICH 11 PRIME button PUSH IN Approximately 3 seconds 12 Throttle CLOSED THEN OPEN INCH 13 Propeller Area CLEAR 14 Ignition Switch START release when engine starts NOTE It may be necessary to leave the boost pump on during starting and turn it off approxi...

Page 47: ...ectrical clutches need to be synchronized by SpeedBrake activation before flight If the SpeedBrakes remain slightly extended this indicates SpeedBrake failure and the SpeedBrake fuse should be pulled BEFORE TAXI 1 Engine Instruments CHECK 2 Fuel Gauges CHECK PROPER INDICATION 3 PFD Annunciations CLEAR 4 Flaps RETRACTED 5 Taxi Clearance AS REQUIRED 6 Lights AS REQUIRED TAXI 1 Toe Brakes CHECK 2 Par...

Page 48: ...roller SET for field elevation 14 Cabin Pressurization Rate Control SET at 12 o clock 15 Fuel Selector Valve FULLEST TANK 16 Oil Temperature ABOVE 100o F 17 Mixture RICH 18 Throttle 1700 RPM 19 Magnetos CHECK RPM drop not to exceed 150 RPM on either magneto or 50 RPM differential between magnetos 20 Propeller CYCLE 2 or 3 times from high to low for a 400 RPM drop return to high RPM Do not exceed 5...

Page 49: ... Reduction 35 MP 2500 RPM Full Rich MAXIMUM PERFORMANCE TAKEOFF CLIMB 1 Lights AS REQUIRED 2 Flaps TAKEOFF POSITION 3 Boost Pump OFF 4 Pitot and Prop Heat AS REQUIRED 5 Brakes APPLY 6 Mixture FULL RICH 7 Propeller HIGH RPM 8 Throttle ADVANCE SLOWLY TO FULL POWER 2700 RPM 9 Brakes RELEASE 10 Elevator Control ROTATE at 70 KIAS 11 Climb Speed 82 KIAS 12 Flaps RETRACT at or above 95 KIAS NORMAL CLIMB ...

Page 50: ...wer 4 Boost Pump LOW above 10 000 ft and as necessary for vapor suppression 5 Fuel Tanks CHANGE PERIODICALLY BOOST PUMP ON DURING CHANGE 6 Cabin Pressurization MONITOR 7 Backup Oxygen MONITOR LEAN OF PEAK ENGINE OPERATION The TSIO 550E engine can be operated lean of peak at power settings of 65 and below Starting from full rich the power increases about 1 as Best Power mixture is reached For cruis...

Page 51: ...T to drop below 300F for periods exceeding five minutes BEFORE LANDING 1 Seats Belts Shoulder Harnesses ADJUST and LOCK 2 Lights AS REQUIRED 3 Fuel Tanks FULLEST TANK PUMP OFF 4 Flaps Takeoff Pos 90 95 KIAS Landing Pos 85 90 KIAS 5 Throttle As desired 14 15 MP 6 Mixture RICH 7 Prop MAX RPM 8 Pressurization CHECK cabin dumped 9 Yaw Damper Autopilot DISENGAGED 10 Speed Brakes RETRACTED APPROACH On t...

Page 52: ...ce is 110 KIAS or greater and with the aircraft stabilized in altitude hold mode At the glideslope intercept adjust power for the desired airspeed For best tracking results make power adjustment in small smooth increments to maintain desired airspeed At 200 feet AGL disconnect the autopilot and continue to manually fly the aircraft to the missed approach point or the decision height If a missed ap...

Page 53: ... an 85 90 KIAS approach speed by establishing a moderately steep nose down attitude BALKED LANDING Go Around 1 Power FULL RICH FULL PROP FULL THROTTLE 38 Hg Max and 2700 RPM 2 Flaps TAKEOFF POSITION 3 SpeedBrakes RETRACT 4 Airspeed 85 KIAS VX 5 Climb POSITIVE Establish Positive Rate of Climb 6 Flaps RETRACT at or above 95 KIAS NORMAL LANDING 1 Touchdown MAIN WHEELS FIRST 2 Landing Roll Lower nose ...

Page 54: ...the flaps in the takeoff position A power descent from a slightly longer than normal final approach is preferred It provides more time to set up and establish the proper crosswind compensation Maintain runway alignment either with a crab into the wind a gentle forward slip upwind wing down or a combination of both Touch down on the upwind main gear first by holding aileron into the wind As the air...

Page 55: ...essurization and control system and air conditioning system The turbocharger bleed air system provides the air supply for pressurizing the cabin Temperature of the bleed air is controlled using an air to air heat exchanger that utilizes ambient air to cool the bleed air The cabin air distribution system consists of side panel ducting windshield defrost foot warmers and an air conditioner The side ...

Page 56: ...ment PRESSURIZATION CONTROLS Cabin pressurization and temperature are controlled through 2 push pull cables an inflatable door seal and a Dukes Cabin Pressurization Controller The two cables operate two separate valves in the Air Mixer Diverter Valve located on the engine firewall The cabin temperature valve is operated by PUSHING the CABIN TEMP control IN for cooler air and PULLING the control OU...

Page 57: ...a 10 000 altitude The warning will appear in the Garmin G900X master warning area The test button for this alarm is located under the instrument panel next to the throttle OPERATION TAKE OFF CLIMB The aircraft can be operated in non pressurized flight by PULLING the CABIN PRESSURE control out which will divert pressurization air overboard this will also deprive the cabin of any heat Although this ...

Page 58: ...ificantly higher drag of the airframe and wings as well as reduced lift and increased weight of the accumulation Once these deposits have been removed preferably by warming in a hangar the preflight should include special emphasis on freedom of control movements ENGINE CONSIDERATIONS Very cold temperatures require extra considerations for engine starting and operations The engine oil will be signi...

Page 59: ...significantly and extreme care must be exercised while ice is present on the airframe It is prudent to avoid icing conditions if at all possible NOISE All approaches and departures should be made with noise considerations second only to safety More and more areas are becoming noise sensitive and our consideration of such areas will prolong our ability to operate in a friendly community environment...

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Page 61: ...F CONTENTS Weights For 8 29 2008 2 Measurements For 8 29 2008 2 Empty Center Of Gravity 3 Full Fuel Center Of Gravity 3 Calculation of Pilot and Copilot Arm 3 Calculation of Rear Passenger Arm 3 Summary 4 Loading Examples 8 29 2008 4 ...

Page 62: ... Lancair ES P construction manual Weights For 8 29 2008 o Leveled by baggage door sill o Full Oil 1 5 gallons per wing for unusable fuel Description Left Right Nose Total Empty 937 911 632 2480 Full Fuel 1204 1182 695 3081 Empty Pilot 1016 957 680 2653 Empty Rear Pax 1037 1008 607 2652 Measurements For 8 29 2008 Measurement Station inches Joggle Under Firewall 51 25 Nose Wheel Axle 51 25 15 5 35 7...

Page 63: ...305648 625 Fuel Arm is 305648 625 240080 5 3081 2480 109 1 Calculation of Pilot and Copilot Arm Item Weight Arm Moment Left Wheel 1016 117 6875 119570 5 Right Wheel 957 117 6875 112626 9375 Nose Wheel 680 35 75 24310 TOTAL 2653 96 686 256507 4375 Co Pilot Arm is 256507 4375 240080 5 2653 2480 94 95 Calculation of Rear Passenger Arm Item Weight Arm Moment Left Wheel 1037 117 6875 122041 9375 Right ...

Page 64: ...RM 94 95 in REAR PASSENGER 129 6 in BAGGAGE 165 in Loading Examples 8 29 2008 Condition CG Pilot 180 Empty Fuel 96 7 Pilot 180 Full Fuel 98 97 Pilot Copilot 600 Empty Fuel 96 44 Pilot 180 Rear Pax 400 Empty Fuel 100 98 Pilot 180 Rear Pax 400 Full Fuel 102 32 Pilot 180 Rear Pax 165 Baggage 175 Empty Fuel 102 47 Pilot 180 Rear Pax 165 Baggage 175 Full Fuel 103 58 ...

Page 65: ...D CONTROL 3 FLAPS 4 SPEED BRAKES 4 LANDING GEAR 4 BAGGAGE COMPARTMENT 5 SEATS BELTS SHOULDER HARNESS 5 CONTROL LOCKS 6 ENGINE 6 GENERAL INFORMATION 6 ENGINE CONTROLS 6 ENGINE STARTING 7 ACCESSORIES 8 FIRE DETECTION EXTINGUISHING 8 ABNORMAL OPERATION 8 PROPELLER 9 FUEL SYSTEM 9 BRAKE SYSTEM 9 ELECTRICAL SYSTEM 10 ...

Page 66: ...E OF ATTACK AOA 12 CO GUARDIAN CARBON MONOXIDE DETECTOR 13 XM WEATHER AND ENTERTAINMENT 14 AVIDYNE TAS610 TCAD 14 CABIN ALTITUDE WARNING SYSTEM 14 HEATING VENTILATING and DEFROSTING 14 PITOT PRESSURE SYSTEM 15 STATIC PRESSURE SYSTEM 15 ...

Page 67: ...and NACA designs with unique airfoils designed specifically for the Lancair mission All primary airfoils are High Laminar flow designs with noncritical characteristics This means that the airfoils are capable of maintaining laminar flow over 50 60 of their chord generating greatly reduced drag Should laminar flow be lost due to surface contamination i e bugs etc no dramatic loss of lift is incurre...

Page 68: ...the SBS fully deployed The SpeedBrakes consist of wing mounted electric brake cartridges with a central controller mounted on the right side fuselage wall The brakes are controlled by a push button switch labeled SPEED BRAKES on the left side of the instrument panel WARNING THE SPEEDBRAKE SHOULD NOT BE USED IN THE FOLLOWING SITUATIONS Forced landing after Engine Failure Spins Ditching Disabled Ele...

Page 69: ...E FLIGHT CONDITIONS FOR EVERY FLIGHT SEATS BELTS SHOULDER HARNESS Front pilot and passenger seats are bucket type with individually adjustable backrests The recliner control is located on the lower inboard corner of each seat To reposition the backrest relieve pressure on the back of the seat and rotate the control In addition to the adjustable backrests the front seats are adjustable fore and aft...

Page 70: ...normally Wheel chocks and tie downs go without saying Another technique that can aid if high winds are expected involves the use of a spanwise spoiler on the wings In all cases be sure to secure such devices in a manner that precludes their coming free and causing damage that they are designed to preclude ENGINE GENERAL INFORMATION A TSIO 550E twin turbocharged fuel injected Continental engine of ...

Page 71: ...The latter provides maximum fuel economy and extended engine life Takeoff is at full rich at all times Increasing the power of the engine should be made right to left across the engine controls mixture full rich RPM as desired finally the throttle increased to the desired manifold pressure Power decreases should be made left to right decrease the manifold pressure reduce the RPM then adjust the mi...

Page 72: ...ts of the extinguisher into the engine compartment via the cooling inlets and remain clear of the aircraft While your aircraft is made of fire resistant materials and its fumes are essentially non toxic it is nonetheless a flying fuel tank and must be treated as such ABNORMAL OPERATION After a few hours of operating this airplane you will become familiar with its operation from its flight controls...

Page 73: ...ne driven fuel pump for delivery to the fuel injector unit A three position fuel selector valve is installed on the floor forward of the pilot and copilot seats The valve controls the selection of OFF LEFT and RIGHT tanks Pull the knob on the valve to select the OFF position An electric boost pump is located on in the copilot footwell behind the kickpanel It is controlled by switches on the contro...

Page 74: ...up alternator These batteries are generally insufficient to power the avionics for any significant time Therefore the MASTER switch should be energized prior to the AUX switch The AUX switch should be switched OFF prior to the MASTER In other words avoid having the AUX switched on without the MASTER BACKUP ATTITUDE INDICATOR The instrument panel includes a Mid Continent 4300 411 electric attitude ...

Page 75: ...ing on standby battery power Restoring aircraft power will clear any standby operation and resume automatic battery charging The battery can be tested during preflight or enroute during normal level flight conditions by pushing and holding the small button on the face of the instrument After about one minute either the Green Test light will appear which means the battery is good or the Red Test li...

Page 76: ...AOA instrument does not meet the FAA TSO requirements for stall warning devices WARNING A failure of the Pitot Static pneumatic system such as taking off with a covered pitot tube will cause the AOA to give false and unreliable information WARNING The AOA Instrument shall never be used as a primary instrument during any flight maneuver It may be used as a backup to primary instruments such as the ...

Page 77: ...ble levels The carbon monoxide alert level is calibrated to provide an alert within five 5 minutes or less whenever the carbon monoxide level reaches 50 parts per million PPM by volume The caution alert time is shortened at higher levels of CO concentrations and becomes almost instantaneous should the carbon monoxide level reach 400 PPM or above The unit becomes active after a three minute 3 senso...

Page 78: ...rs XM Satellite Radio A wide variety of continuous news sports music and entertainment programming is available anywhere nationwide The GDL 69A interfaces with the audio panel to play through the aircraft s audio system AVIDYNE TAS610 TCAD This aircraft includes an Avidyne TAS610 traffic proximity warning system It consists of antennas on the top and bottom of the fuselage a traffic computer under...

Page 79: ...atures IMC conditions or precipitation a check of the pitot heater must be made prior to flight This check can be made during preflight by turning the master switch on the pitot heater power on for a few seconds less than 10 typically and then feeling the probe for warmth The preflight must also check that the probe opening has not become home for a wasp and that any cover has been removed NOTE Pr...

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Page 81: ... REQUIRED INSPECTIONS 4 RECOMMENDED INSPECTIONS 4 ALTERATIONS OR REPAIRS 5 GROUND HANDLING 5 TOWING 5 TIE DOWNS 6 MAIN WHEEL JACKING 6 NOSE WHEEL JACKING 6 OUT OF SERVICE CARE 6 FLYABLE STORAGE 7 PREPARATION FOR SERVICE 7 FUEL SERVICING 7 OIL SYSTEM SERVICING 7 OIL CHANGES 8 BATTERIES 8 TIRES 8 NOSE GEAR SHOCK STRUT 8 BRAKES 9 PROPELLER 9 ELECTRICAL POWER 9 ...

Page 82: ...CARE AND CLEANING 10 EXTERIOR PAINTED SURFACES 11 ENGINE 11 RECOMMENDED SERVICING 12 ...

Page 83: ...ied repair station before the plane can be flown All limits procedures safety practices servicing instructions and requirements contained in this handbook should be considered mandatory It is strongly recommended that you secure the services of an FBO familiar with Lancairs or at least this type of amateur built aircraft for support This will benefit both you as the owner and the FBO by becoming y...

Page 84: ...IV of this handbook be made These are at 25 hour and 100 hour intervals Your new aircraft will undoubtedly be given several 100 hour inspections at earlier intervals a practice which is also recommended In addition there are continuing care items items which have a recommended overhaul or replacement schedule and special inspections required due such as gear flap extensions at high speeds The 25 h...

Page 85: ...tely defined and determined acceptable by Lancair are not acceptable and are considered unsafe for use GROUND HANDLING The three view drawings in Section II show the dimensions of this aircraft and its hangar requirements CAUTION Proper inflation of the air oleo style nose strut should be maintained to insure adequate propeller clearance In addition while ground handling your Lancair the propeller...

Page 86: ...ist to the engine lifting ring then raise the nose as desired watch the spinner Again care must be observed and the caution note above applies OUT OF SERVICE CARE Should you be required to place your Lancair in storage precautions to protect it from deterioration are recommended If long term storage is required protection from the elements is the primary concern With the Lancair it may be easiest ...

Page 87: ...ons for flight should include the following Remove all taped openings plugs and control locks Clean and thoroughly inspect the aircraft checking the gear tires controls pitot and static ports Install a serviced battery Install spark plugs and check the oil level The preservative oil used for storage should be removed and proper oil installed The fuel tanks should be checked for water accumulation ...

Page 88: ...ry from aluminum to steel to stainless steel Following the initial break in period during which some metallic particles are normal almost any amount becomes cause for concern If subsequent changes show additional metallic particles the source should be determined The type can be somewhat determined by separating by category i e magnetic or not steel or aluminum silicon sand etc BATTERIES The batte...

Page 89: ...serviced The brake pucks should be at least 0 150 inches thick and should be replaced when less than this value PROPELLER The propeller should be serviced according to MT s instructions It is a highly stressed component and any failure has the potential of being catastrophic Treat it with care The MT propeller is sensitive to leading edge damage and possible erosion shield delamination Refer to th...

Page 90: ...tone carbon tetrachloride anti ice fluids lacquer thinners or glass cleaners They will either soften the material or cause it to craze Rubbing of the surface with a dry cloth should be avoided as its causes static electricity build up which subsequently attracts dirt and dust particles WARNING The windows are a bonded in part of this aircraft and are extremely difficult and time consuming to repla...

Page 91: ... probes and static ports Cover cooling ports to the interior and avionics ENGINE Clean the engine with a neutral solvent While the engine is warm but not hot spray with solvent and allow setting a few minutes Follow with a spray wash and allow to dry Avoid excessively high pressures which can force entry of water and or solvents under seals resulting in contamination of the sealed system or entry ...

Page 92: ... LANDING GEAR FAIRINGS CHECK CONTROL SURFACE HINGES EACH 50 HRS CHANGE OIL CLEAN OR CHANGE ENGINE AIR FILTER CHECK CONTROL SURFACE HINGES EACH 100 HRS CHANGE ENGINE OIL CHANGE OIL FILTER CLEAN FUEL STRAINERS HOSES WEAR TIGHTNESS NO CRACKS CHECK COWLING ATTACH FASTENERS CHECK ATTACH POINTS CLEAN CHANGE ENGINE AIR FILTER CHECK ENGINE MOUNTS CHECK AIRBOX ALTERNATE AIR DOOR SECUR1TY NO CRACKS EXHAUST ...

Page 93: ...XLINES CHECK FOR CHAFING FLAP ACTUATOR CHECK SECURITY WEAR FLAP TO AIRCRAFT FIT EXCESSIVE RUBBING WEAR AILERON TO FLAPS AND WING FIT FOR RUBBING WEAR RUNNING LIGHTS AND STROBES STATIC SYSTEM LEAK TIGHT X PONDER FUNCTIONAL DOOR ATIACH POINTS MECHANISM SECURE SHOULDER HARNESS ATIACH POINTS SECURE FRAYING MATERIAL SEAT BELTS ATTACH POINTS SECURE FRAYING MATERIAL AIRFRAME DELAMINATIONS CRACKS LOST PAI...

Page 94: ......

Page 95: ...SECTION 9 SUPPLEMENTS TABLE OF CONTENTS ALTITUDE REGULATIONS 2 ALTITUDE REACTION 2 ...

Page 96: ...Level 250 In the short version we need supplemental oxygen from 12 500 to 14 000 if we stay there more than 30 minutes If we go higher than 14 000 for any length of time oxygen is required And of course we must provide passengers with supplemental oxygen above 15 000 feet If the aircraft is pressurized and operates above FL250 then a further requirement of at least 10 minutes supplemental oxygen p...

Page 97: ...supplemental oxygen hypoxia is almost immediately apparent and efficiency deteriorates quickly and drastically Unconsciousness can occur if supplemental oxygen is not used 20 000 Unconsciousness can occur in as little as 5 7 minutes without supplemental oxygen 25 000 Hypoxia rate increases rapidly usually less than 5 minutes of consciousness without supplemental oxygen 28 000 Immediate 100 loss of...

Page 98: ......

Page 99: ...N 2 GENERAL 2 FIRST FLIGHT 3 SOURCES OF INFORMATION 3 AIRMAN S INFORMATION MANUAL 4 ADVISORY INFORMATION 4 FAA ADVISORY CIRCULARS 4 FLIGHT PLANS 5 MOUNTAIN FLYING 5 SEVERE WEATHER 6 ICING 6 MARGINAL VFR FLIGHT 7 NIGHT FLYING 7 VERTIGO HYPOXIA 7 ENGINE FAILURE 9 ...

Page 100: ...t to flight This will allow you to correct minor problems so they don t become major ones Skill results when you continuously set tougher and tougher standards for yourself as you operate the aircraft Fly smoother today than you did yesterday Be more precise on lift off speed today and hold climb speed closer Predict you and your aircraft s performance and understand why you were not quite on the ...

Page 101: ...iew the flight from takeoff thru landing for speeds and altitudes Rotate at___kts climb at___kts level off at___feet etc Is all equipment operative for the flight Lights transponder flashlight batteries plus spares life vests for that cut across the lake first aid kit just in case sickness bags for that novice passenger maps approach plates for destination and alternates enroute etc At big airport...

Page 102: ...ISORY INFORMATION Notices to Airmen NOTAMs provide information of a time critical nature which can affect the decision to go or not go for example a closed airport navaids out of service runway closures etc FAA ADVISORY CIRCULARS These circulars are the FAA s means of informing the flying public of non regulatory items of interest They cover a myriad of subjects and can be obtained at FAA offices ...

Page 103: ...ould always know where and when you are going and by what route Enroute an occasional weather check for the destination is prudent if there is anything but severe clear in the area Since your Lancair has long legs you can well expect significant weather changes between takeoff and landing both in terms of temperatures and types of weather Over deserts in the summer calls for carrying some drinking...

Page 104: ...anything man can build he can break Severe weather means dangerous wind shears and vertical air movements These can often be seen as evidenced by cumulus or lenticular clouds but not always Winters can lower the jet stream into our flight altitudes where wind shears can result in clear air turbulence Should surprise add some adrenaline into the picture over stressing could be a problem ICING The E...

Page 105: ...ght flights and for good reason Forced landings off airports are problematical at best Clouds are hard to see ahead and in some locations there are as many stars in the sky as lights on the ground and which way is up becomes a problem without reference to the instruments Use the MEAs for altitudes flying enroute and approach plates for terminal area altitudes and flight paths and be on the alert f...

Page 106: ...ol is serious an accident is almost inevitable Hypoxia is a dangerous condition It is not limited to VFR pilots IFR rated pilots who are not up to par because of medicines mental stress turbulence or other condition are also subject to the condition All pilots should be particularly wary of and on the lookout for these symptoms their lives and the lives of their passengers depend on it Hyperventil...

Page 107: ...l thru initial impact and until the aircraft comes to rest Should you ever have this unfortunate occurrence you ll be happy you used the entire runway available rather than making the takeoff from the intersection to avoid the long taxi to the far end of the field Again on the positive side engine failures without warning are extremely rare Being mechanical devices there is almost always some warn...

Page 108: ......

Page 109: ...TURBOS 4 COMPRESSORS 4 PROPELLER GROUP 4 CABIN AND COCKPIT GROUP 5 WING GROUP 6 EMPENNAGE GROUP 7 ELECTRICAL SYSTEM 7 LANDING GEAR GROUP 8 FUEL SYSTEM 9 FUSELAGE AND HULL GROUP 9 RADIO GROUP INSTALLATION 10 EMERGENCY LOCATOR TRANSMITTER 10 MISCELLANEOUS GROUP 11 ITEMS REQUIRED FOR FLIGHT 11 WORK PERFORMED 12 POWER PLANT OPERATIONAL PREFLIGHT CHECK 13 ...

Page 110: ...ction for evidence of fuel oil and hydraulic leaks Check the aluminum baffle for contact around inlet area _____2 Drain oil while engine is warm Replace oil filter and drain plug Refill oil sump _____3 Check internal conditions of engine by compression while hot 1 80 2 80 3 80 4 80 5 80 6 80 _____4 Remove clean and regap spark plugs Rotate plugs from upper to lower positions and lower to upper pos...

Page 111: ...effort required to check and adjust the magnetos will be rewarded by longer contact point and spark plug life A smoother running engine requiring less maintenance will be the result _____14 Check fuel injection system for loose fittings chafing _____15 Check alternator and or generator make sure wires are tight and are not chaffing _____16 Check pressure mixing box and valve _____17 Wash down engi...

Page 112: ...on the compressor for freedom of movement and condition COMPRESSORS _____1 Duct tape the exhaust side of a vacuum into the Compressor side of the induction system Remove the sceet tubing from the mixer or heat valve Plug the end of the skeet tubing Check the Compressor and induction system for leaks also check the bleed air and after coolers for leaks PROPELLER GROUP _____1 Inspect propeller blade...

Page 113: ... compliance _____11 Check spinner backing plate and brackets Install spinner CABIN AND COCKPIT GROUP _____1 Check brake master cylinders for leaks security and fill with fluid _____2 Check Cabin latches handles chains and sprockets for condition and security Lubricate _____3 Inspect cabin and cockpit for loose equipment which might foul controls _____4 Inspect back of instrument panel for security...

Page 114: ...__18 Clean the interior of the airplane _____19 Check heating and ventilating system _____20 Check boost pump for fuel stains and attachment _____21 Inspect cabin door locks and hinges Remove one hinge at a time and inspect hinge pin for condition Lubricate and install pins and hinge _____22 Inspect hydraulic lines for leaks WING GROUP _____1 Check surface of skin for general condition deteriorati...

Page 115: ...hments and adjacent areas _____3 Check rudder cables for chafing and condition and safety _____4 Check trim tabs for excessive looseness and proper operation _____5 Inspect rudder and elevator hinge fittings and pins for cracks looseness and proper installation _____6 Operate rudder and elevator Check for ease of operation and proper travel and stops _____7 Inspect the trim tabs and push rods for ...

Page 116: ...oor seal pump for condition _____11 Check cabin controller and outflow valve for operation and condition _____12 Evaluate the calibration and or service needs of the CO Guardian carbon monoxide detector LANDING GEAR GROUP _____1 Inspect landing gear for general condition and security of attachment _____2 Check condition of nose strut _____3 Check all linkage trusses and members for evidence of exc...

Page 117: ...Check both tanks and filler caps _____2 Drain sumps _____3 Check all fuel lines for leaks at connections and security of mounting _____4 Check fuel tank vents _____5 Check condition and operation of fuel tank selector valve _____6 Check placard at fuel tank filler caps FUSELAGE AND HULL GROUP _____1 Check surface condition of skin for general condition deterioration distortion cracks and other evi...

Page 118: ...ing _____4 Check bonding and shielding for proper installation and condition _____5 Check all antennas for condition and security of mounting EMERGENCY LOCATOR TRANSMITTER _____1 Check batteries and note the date they should be replaced _____2 Remove ELT from A C Install Portable Antenna Test between 5 min to the hour and 5 min after the hour _____3 Lightly tap the ELT into your other hand increas...

Page 119: ... and proper operation _____2 Compass correction card in view of pilot ITEMS REQUIRED FOR FLIGHT _____1 Airworthiness Certificate _____2 Registration _____3 Operating Manual _____4 Weight and Balance _____5 Fuel Grade and capacity by filler cap _____6 Passenger warning in cabin _____7 Experimental on door _____8 Identification on tail ...

Page 120: ...WORK PERFORMED ...

Page 121: ..._____________________________________ TIME _________________________________________ Warm up engine and check the following Generator Alternator output Oil Pressure Oil Temperature Fuel Pressure Head Temperature Magnetos Left drop_______ right drop_______ Run propeller thru range Check all engine controls Brakes and parking brakes Idle rpm ...

Page 122: ...Idle cut off Static rpm Idle mixture Check engine for oil leaks ...

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