Lancair IV User manual

Lancair IV
HANDBOOK TABLE OF CONTENTS
SECTION I
GENERAL 2
SECTION II
LIMITATIONS 11
SECTION III
EMERGENCY PROCEDURES 16
SECTION IV
NORMAL PROCEDURES 23
SECTION V
WEIGHT AND BALANCE 33
SECTION VI
SYSTEMS DESCRIPTION 37
SECTION VII
HANDLING, SERVICE and
MAINTENANCE 48
SECTION VIII SUPPLEMENTS 60
General
Section I
Table of Contents
IMPORTANT NOTICE 3
REVISING THIS HANDBOOK 4
DESCRIPTIVE DATA 5
Engines
Propellers
Fuels
Oil Capacities
Weights
Cabin and Entry Dimensions
Baggage
 SpecicLoading(MaxTake-oWeight)
GEN. AIRSPEED
TERMINOLOGY/SYMBOLS 6
METEROLOGICAL TERMINOLOGY 7
POWER TERNINOLOGY 7
ENGINE CONTROLS/INSTRUMENTS 8
PERFORMANCE AND
FLIGHT PLANNING TERMINOLOGY 8
WEIGHT AND BALANCE TERMINOLOGY 9

THANK YOU......
Youhaveobtainedwhatwefeelisthelateststate-
of-the-artinahighperformancegeneralaviationair-
craft. Its performance is spectacular and its life almost
beyond measure given reasonable care. A team of out-
standing craftsmen has been assembled to design and
produce quality aircraft components which can serve
you well for years to come. We encourage you to be-
comefamiliarwiththishandbookaswellastheFAR’s
that are applicable to your operation. The combination
willprovideyouwithsafeandsoundknowledgefor
operation of your personally manufactured Lancair.
IMPORTANT NOTICE
 Thishandbookmustbereadcarefullybythe
owneroroperator(s)ofyourLancairinordertobecome
familiar with its operation and to obtain all it has to
oerintermsofbothspeedandreliability.Hereinare
suggestions and recommendations to help you obtain
safeperformancewithoutsacricingeconomy.Youare
encouraged to operate your machine in accordance with
andwithinthelimitsidentiedinthisPilot’sOperating
Handbookaswellasanyplacardslocatedintheair-
plane.
 Again,anotherreminder-theoperatorshould
also be familiar with the Federal Aviation Regulations
asapplicabletotheoperationandmaintenanceofex-
perimental airplane and FAR Part 91 General Operating
and Flight Rules. The aircraft must be operated and
maintained in accordance with any FAA Airworthiness
Directives which may be issued against it. It is also
prudent and mandatory to operate within any estab-
lished limits or Service Bulletins.
The FARs place the responsibility for the main-
tenance of this airplane on the owner and the operator
who must ensure that all maintenance is accomplished
bytheownerorqualiedmechanicsinconformity
with all airworthiness requirements established for this
airplane.
All limits, procedures, safety practices, time
limits, servicing, and maintenance requirements con-
tainedinthishandbookareconsideredmandatoryfor
the continued airworthiness of this airplane, in a condi-
tion equal to that of its original manufacture.
Authorized Service Facilities can provide
recommended service, repair, or operating procedures
issued by both the FAA and Lancair International to ob-
tainthemaximumprudentusefulnessandsafetyfrom
your Lancair.

NOTE
Except as noted, all airspeeds quoted in this
handbook are Indicated Airspeeds (IAS) in Knots
and assume zero instrument error.
Inaneorttoprovideascompletecoverageaspossi-
ble, some optional equipment has been included in the
scopeofthishandbook.Howeverduetothevariety
ofairplanecongurationsavailable,someequipment
described and depicted herein may not be included on
yourspecicairplane.
The following information may be provided to the hold-
er of this manual automatically:
1. Original issues and revisions of Service Bulletins
2. Original issues and revisions of Lancair Approved
Airplane Flight Manual Supplements
This service is available and will be provided only to
holdersofthishandbookwhoarelistedontheLancair
Owner/Builder List and then only if listed by airplane
serialnumberforthemodelforwhichthishandbook
is applicable. Detailed information on this “Revision
Service” can be obtained from Lancair.
NOTICE
LANCAIR INTERNATIONAL INCORPO-
RATED EXPRESSLY RESERVES THE RIGHT
TO SUPERSEDE, CANCEL AND/OR DECLARE
OBSOLETE, WITHOUT PRIOR NOTICE, ANY
PART, PART NUMBER, KIT OR PUBLICATION
REFERENCED HEREIN.
The owner/operator should frequently refer to all
supplements,whetherSTCs(SupplementalTypeCertif-
icate)orLancairSupplementsdirectfromLancair,for
appropriate placards, limitations, normal, emergency
and other operational procedures for proper operation
of their Lancair with any optional equipment installed.
REVISING THIS HANDBOOK
WARNING
When this handbook is used for airplane op-
erational purposes, it is the pilots responsibility to
maintain it in current status.
NOTE
Upon receipt of a new 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.

DESCRIPTIVE DATA
ENGINES
 TheLancairIVcanbettedwiththefollowing
engines:
 ContinentalTSIO-550B
 ContinentalIO-550G
Although other engines are available, we feel
these engines will give you the best performance and
are the latest designs from Continental. Aircraft perfor-
mance will of course vary with the engine selection.
PROPELLERS
The Lancair IV uses a MT , 76”, 3 bladed con-
stant speed propeller. Propeller governors are made by
McCauley,LancairPN.D20309-39.
Lancair is constantly testing other propellers that may
improve performance and/or serviceability, we will
publishthesendingswhentheyareavailable.
NOTE
Other propellers which are approved are
listed by Lancair and its dealers or are approved by
Supplemental Type Certicates.
FUELS
 100or100LL(MinimumgradeAviationGas-
olineconformingtoASTMD910-76&MIL-G-5572,
latestrev.)
STANDARD SYSTEMS CAPACITIES
Standard fuel capacity 80 US Gal.
Long range option 90 US Gal.
OIL CAPACITY 12 Qts.
WEIGHTS
Maxgrosstakeo    
3200
Maxlandingweight    
2900
Maxweightinbaggagecompartment 150
CABIN AND ENTRY DIMENSIONS
Length 126 inches
Height(max)     48inches
Width
front seat 46 inches
rear seat 43 inches
BAGGAGE Compartment Volume
    Approx.13.5Cu.Ft.
SPECIFICLOADING(maxtake-oweight)
Wing loading 32.65 lb./sq. ft.
Powerloading(350h.p.)  9.14lb./h.p.

SPECIFICLOADING(maxtake-oweight)
Wing loading
32.65 lb./sq. ft.
Powerloading(350h.p.)   
9.14 lb./h.p.
GENERAL AIRSPEED TERMINOLOGY
AND SYMBOLS
CAS Calibrated Airspeed is the indicated speed of an
airplane, corrected for “position error” and instrument
error. Calibrated airspeed is equal to true airspeed in
standard atmosphere at sea level.
GS Ground Speed is the speed of an airplane rela-
tive to the ground.
IAS Indicated Air Speed is the speed of an airplane
as shown on the airspeed indicator when corrected
for instrument error. IAS values published in this hand-
bookassumeszeroinstrumenterror.
KCAS CalibratedAirspeedexpressedin“knots”.
KIAS IndicatedAirspeedexpressedin“knots”.
TAS True Airspeed is the airspeed of an airplane rel-
ative to undisturbed air which is the CAS corrected for
altitude, temperature and compressibility.
V
A ManeuveringSpeedisthemaximumspeedat
which application of full available
aerodynamic control will not overstress the air-
plane.
VFE MaximumFlapExtendSpeedisthehighest
speedpermissiblewithwingapsinaprescribedex-
tended position.
VLE MaximumLandingGearExtendedSpeedis
themaximumspeedatwhichanairplanecanbesafely
ownwiththelandinggearextended.
VLO MaximumLandingGearOperatingSpeedisthe
maximumspeedatwhichthelandinggearcanbesafely
extendedorretracted.
VNE NeverExceedSpeedisthespeedlimitthatmay
notbeexceededatanytime.
VNO/VCMaximumStructuralCruisingSpeedis
thespeedthatshouldnotbeexceededexceptinsmooth
air and then only with caution.
VS StallingSpeedortheminimumsteadyight
speed at which the airplane is controllable.
GENERAL AIRSPEED TERMINOLOGY
AND SYMBOLS
CAS Calibrated Airspeed is the indicated speed of an
airplane, corrected for “position error” and instrument
error. Calibrated airspeed is equal to true airspeed in
standard atmosphere at sea level.
GS Ground Speed is the speed of an airplane rela-
tive to the ground.
GENERAL AIRSPEED TERMINOLOGY

AND SYMBOLS
CAS Calibrated Airspeed is the indicated speed of an
airplane, corrected for “position error” and instrument
error. Calibrated airspeed is equal to true airspeed in
standard atmosphere at sea level.
GS Ground Speed is the speed of an airplane rela-
tive to the ground.
IAS Indicated Air Speed is the speed of an airplane
as shown on the airspeed indicator when corrected
for instrument error. IAS values published in this hand-
bookassumeszeroinstrumenterror.
KCAS CalibratedAirspeedexpressedin“knots”.
KIAS IndicatedAirspeedexpressedin“knots”.
TAS True Airspeed is the airspeed of an airplane rel-
ative to undisturbed air which is the CAS corrected for
altitude, temperature and compressibility.
V
A ManeuveringSpeedisthemaximumspeedat
which application of full available
aerodynamic control will not overstress the air-
plane.
VFE MaximumFlapExtendSpeedisthehighest
speedpermissiblewithwingapsinaprescribedex-
tended position.
VLE MaximumLandingGearExtendedSpeedis
themaximumspeedatwhichanairplanecanbesafely
ownwiththelandinggearextended.
VLO MaximumLandingGearOperatingSpeedisthe
maximumspeedatwhichthelandinggearcanbesafely
extendedorretracted.
VNE NeverExceedSpeedisthespeedlimitthatmay
notbeexceededatanytime.
VNO/VCMaximumStructuralCruisingSpeedis
thespeedthatshouldnotbeexceededexceptinsmooth
air and then only with caution.
VS StallingSpeedortheminimumsteadyight
speed at which the airplane is controllable.
VSO StallingSpeedortheminimumsteadyight
speed at which the airplane is controllable in the land-
ingconguration.
VX BestAngle-of-ClimbSpeedistheairspeed
which delivers the greatest gain of altitude in the short-
est possible horizontal distance.
VY BestRate-of-ClimbSpeedistheairspeedwhich
delivers the greatest gain in altitude in the shortest pos-
sible time.
METEOROLOGICAL TERMINOLOGY

GPH Gallonsperhourfuelow.
PPH Poundsperhourfuelow.

ISA International Standard Atmosphere in which
 1)Theairisadryperfectgas;
 2)Thetemperatureatsealevelis15oCelsius
(59o 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-0.00198oC
(-0.003566oF)perfootandzero
above that altitude.
OAT (Outside Air Temperature) The free air static
temperature,obtainedeitherfrominighttemperature
indicators adjusted for instrument error and compress-
ibilityeects,orgroundmeteorologicalsources.
Indicated Pressure Altitude The number actually read
from an altimeter when the barometric subscale has
been set to 29.92 in Hg or 1013.2 millibars.
Pressure Altitude Altitude measured from standard
sea-levelpressure(29.92inHg)byapressureorbaro-
metric altimeter. It is the indicated pressure altitude
corrected for position and instrument error. In this
handbook,altimeterinstrumenterrorsareassumedtobe
zero. Position errors may be obtained from the Altime-
ter Correction Graph.
Station Pressure Actualatmosphericpressureateld
elevation.
Wind The wind velocities recorded as variables on the
chartsofthishandbookaretobe understoodas
the headwind or tailwind components of the reported
winds.
POWER TERMINOLOGY
Take-o and Maximum Continious The highest pow-
er rating not limited by time.
Cruise Climb The power recommended for cruise
climb.
ENGINE CONTROLS/INSTRUMENTS
Throttle Control Used to control power by introduc-
ingfuel-airmixtureintotheintakepassagesoftheen-
gine.Settingsarereectedbyreadingsonthemanifold
Pressure gauge.
Propeller Control This control requests the propeller
to maintain engine/propeller rpm at a selected value by
controlling blade angle.
Mixture ControlThiscontrolisusedtosetfuelow
inallmodesofoperationandcuts ofuelcomplete-
ly for engine shutdown.
EGT (Exhaust Gas Temperature) This indicator is
usedtoidentifytheleanandbestpowerfuelowfor
various power settings.
CHT (Cylinder Head Temperature) The indicator
used to identify the operating temperature of the en-
gines’cylinder(s).

Climb Gradient The ratio 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 demonstrat-
ed crosswind velocity is the velocity of the crosswind
component for which adequate control of the airplane
duringtake-oandlandingwasactuallydemonstrat-
ed. The value shown is considered to be limiting. The
valueinthishandbook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identiedby:
  1)ageographicallocation;or
  2)apointatwhichadeniteradiox
can be established.
GPH Gallonsperhourfuelow.
PPH Poundsperhourfuelow.
WEIGHT AND BALANCE
TERMINOLOGY
TIT Thetemperatureoftheexhaustgassesasthey
enter the respective turbocharger.
copydatafrompagesI-14throughI-18
Tachometer Indicates the rpm of the engine/propeller.
Propeller Governor Regulates the rpm of the engine/
propeller by increasing or decreasing the propeller pitch
through a pitch change mechanism in the propeller
hub.
PERFORMANCE AND FLIGHT
PLANNING TERMINOLOGY

Reference Datum An imaginary vertical plane from
which all horizontal distances are measured for balance
purposes.
Station A location along the airplane fuselage usually
given in terms of distance from the reference plane.
Arm The horizontal distance from the reference da-
tumtothecentergravity(CG)ofanitem.
Moment The product of the weight of an item multi-
pliedbyitsarm.(Momentdividedbyaconstantmay
be used to simplify balance calculations by reducing the
number of digits.
Airplane Center of Gravity (CG) 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 Fuel Thefuelavailableforightplanning
purposes.
Unusable Fuel Fuel remaining after a runout test has
been completed in accordance with governmental regu-
lations.
Standard Empty Weight Weight of a standard air-
planeincludingunusablefuel,fulloperatinguidsand
full oil.
Basic Empty Weight Standard empty weight plus any
optional equipment.
Payload Weight of occupants, cargo and baggage.
Useful Load Dierencebetweentake-oweightor
ramp weight if applicable and basic empty weight.
Maximum Ramp Weight Maximumweightapproved
forgroundmaneuvering.(Itincludesweightofstart,
taxiandrunupfuel).
Maximum Take-O WeightMaximumweightap-
provedforthestartofthetake-orun.
Maximum Landing Weight Maximumweightap-
proved 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identiedbythe
manufacturer as suitable for supporting the airplane
for weighing or other purposes.
ler.
Propeller Governor Regulates the rpm of the engine/
propeller by increasing or decreasing the propeller pitch
through a pitch change mechanism in the propeller hub.
PERFORMANCE AND FLIGHT
PLANNING TERMINOLOGY
Climb Gradient The ratio 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 demonstrat-
ed crosswind velocity is the velocity of the crosswind
component for which adequate control of the airplane
duringtake-oandlandingwasactuallydemonstrated.
The value shown is considered to be limiting. The value
inthishandbook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identiedby:
  1)ageographicallocation;or
  2)apointatwhichadeniteradiox
can be established.
Throttle Control Used to control power by intro-
ducingfuel-airmixtureintotheintakepassagesof
theengine.Settingsarereectedbyreadingsonthe
manifold Pressure gauge.
Propeller Control This control requests the pro-
peller to maintain engine/propeller rpm at a selected
value by controlling blade angle.
Mixture Control This control is used to set fuel
owinallmodesofoperationandcuts ofuel
completely for engine shutdown.
EGT (Exhaust Gas Temperature) This indicator is
usedtoidentifytheleanandbestpowerfuelowfor
various power settings.
CHT (Cylinder Head Temperature) The indica-
tor used to identify the operating temperature of the
engines’cylinder(s).
TIT Thetemperatureoftheexhaustgassesasthey
enter the respective turbocharger. Copy data from
pagesI-14throughI-18
Tachometer Indicates the rpm of the engine/propel-

Limitations
Section II
Table of Contents
GENERAL 12
AIRCRAFT OPERATING SPEEDS 12
POWERPLANT LIMITATIONS 12
OPERATING LIMITATIONS 12
OIL SPECIFICATIONS 13
PROPELLERS 13
POWERPLANT INSTRUMENTS MARKINGS 13
MISC INSTRUMENT MARKINGS 14
HYDRAULIC PRESSURE 14
WEIGHT LIMITS 14
CENTEROFGRAVITYLIMITS(GearExtended) 14
REFERENCE DATUM 15
FLIGHT LOAD FACTOR LIMITS 15
TYPES OF OPERATIONS AND LIMITS 15
FUEL QUANTITIES 15
SEATING 15
WINTER OPERATIONS 15
GENERAL
The data approved by Lancair International and
the limitations presented herein are those established by
Lancair as applicable to the Lancair IV model aircraft.
The airspeeds quoted are given conventional nomen-
clature,areshowninknots,calibratedairspeed,and
assumes zero instrument error.
NOTE
It is imperative that you calibrate your airspeed
system (static and pitot) to provide the corrections to
the values shown below in KCAS. There is instru-
ment (gauge) error that needs to be factored in also
to reach KIAS
AIRCRAFT OPERATING SPEEDS
SPEED MARKING KCAS
Neverexceedspeed VneRedLine 274
Caution,smoothaironly YellowArc 220-274
Maneuvering Speed Va 170
NormalOperatingrangeVnoGreenArc 69-220
FlapOperatingrange,0-10Deg  174
FlapOperatingrange, Vfe WhiteArc 61-
132
BestAngleofclimbspeedVx  110
Best Rate of climb speed Vy 135
Stall Speed clean Vs 69
StallSpeedlandingcong.Vso  61
Landing Gear Operating speed Vlo 150
LandingGearExtendedSpeedVle  165

POWERPLANT LIMITATIONS
The Lancair is typically powered with the Continental
TSIO-550B,350h.p.,sixcylinderhorizontallyopposed,
fuel injected, air cooled, twin turbocharged and twin
intercooled engine.
OPERATING LIMITATIONS
OperatinglimitationsfortheTSIO-550Bengineislist-
edbelow.Ifyourenginediers,youmustaccountfor
that. In addition, the data and limits shown are for new
specicationenginesanddonotreectanydegradation
due to age or number and quality of overhauls.
Maxcontinuous,BHP(-0.+5)RPM. 350-2700
MaxcontinuousManifoldPressure  38”Hg.
Maxrecommendedclimb-BHP/RPM 262/2500
MaxrecommendedCLIMBmanifoldpress.31.0”Hg.
CylinderHeadTemperatures-Deg.F.
 Maximum    460.
 Min.,Max.LimitatMaxcruise 380-420
OilTemperatures-Deg.F.
 Maximum    240
 RecommendedTake-oMinimum 100
 Min.,Max.Limit-MaximumCruise 160-180
OilPressure-PSI
 Normaloperation   30-60
Idle, Minimum 10
 MaxAllowable(coldoil)  100
Fuel Flow
Fuel Flow vs. Horsepower See Model Spec
sheets.
FuelPressure(Unmeteredp.s.i.g.)
 Idle(700RPM)   7.0-9.0
 Takeo    32-34
Vacuum Pressure
 Normaloperatingrange,In.Hg. 4.8-5.2
FuelGrades(AviationGasoline) 100or100LL
OIL SPECIFICATION
OilusedmustconformtoTeledyneContinentalMotors’
specicationMHS-24,orMHS-25latestrevision.
PROPELLERS
The Lancair IV uses a Hartzell or MT 3 bladed con-
stant speed propeller. Propeller governors are made by
McCauley,Lancairpart#D20309-39.
Maximumrecommendedpropellerdiameteris78”and
aMaximumweightof75#
Lancair is constantly testing other propellers that may
improve performance and/or serviceability, we will
publishthesendingswhentheyareavailable.

POWERPLANT INSTRUMENT
MARKINGS
Itisrecommendedthatthefollowingmarkingsbemade
on the engine instrument gauges to conform to conven-
tion.
NOTE
Continental TSIO-550 B values shown. The owner/
operator should compare and correct (where dier-
ent) for the particular model specications for his
installation.
OIL TEMPERATURE (Deg.F.)
Caution(Yellowradial)   180-240
NormalOperatingrange(Greenarc)  160-180
Maximum(Redline)    240
RecommendedTakeoMinimum  100
OIL PRESSURE (PSI)
Minimum(Idle,Redline)   10
CautionRange(Yellowarc)   10-30
OperatingRange(Greenarc)   30-60
Maximum(RedLine)   100
TACHOMETER (RPM)
OperatingRange(GreenArc)  600-2700
Maximum(RedLine)   2700
CYLINDER HEAD TEMP. (Deg.F)
OperatingRange(GreenArc)  380-420
Maximum(RedLine)   460
TURBINE INLET TEMP (Deg.F)
Max.Continuous(GreenArc)  1750
Peak-30Secondlimit(RedLine)  1800
MANIFOLD PRESSURE(In.Hg.)
Operatingrange(GreenArc)   15-38
Maximum(RedRadial)   38
FUEL FLOW (PSIG)
Operatingrange(GreenArc)   7-34
MaximumPressure(RedRadial)  34
MISC. INSTRUMENT MARKINGS
VACUUM PRESSURE (In.Hg.)
OperatingRange(GreenArc)  4.8-5.2
HYDRAULIC PRESSURE (psi)
Normal System Pressure 1000
Accumulatorpre-charge   700
WEIGHT LIMITS (lbs)
MaximumTake-OWeight   3200
MaximumLandingWeight   2900
MaximumBaggageWeight   150
CENTER OF GRAVITY LIMITS (Gear Ex-
tended)
TheallowableCenterofGravity(CG)rangeisfrom
FuselageStation(FS)86.5to(FS)94.5or8.0to27.5%
MAC.

AFT LIMIT
The aft CG limit is at FS 94.5 inches and must be con-
sideredarmlimit.LoadswhichplacetheCGfurther
aft are dangerous and must not be accepted. A “Weight
and Balance” sheet must be completed and carried in
the aircraft at all times.
REFERENCE DATUM
The Datum is located at FS “0”. This can be located by
measuring 51.25” forward of the bottom forward face
oftherewall.
MEAN AERODYNAMIC CHORD.
The MAC corresponding to the CG limits of 86.5 and
94.5are8.0%and27.5%respectfully.
FLIGHT LOAD FACTOR LIMITS
FlapsUp    +4.4,to-2.3g’s.
FlapsDown    +3.8,to-2.0g’s
TYPES OF OPERATIONS AND LIMITS
The Lancair IV is approved for the following types of
ightwhentherequiredequipmentisinstalledandop-
erationsareconductedasdenedintheLIMITATIONS
section.
1. VFR, day and night
 2.IFR,day;andnight
Warning
1. Flight operations with passengers for hire
and
 2.Flightintoknownicingisprohibited.
FUEL QUANTITIES (U.S.Gal.)
Standard fuel 80
ExtendedFueloption     90
FUEL MANAGEMENT
Donottakeowithlessthan10gallonsineachtank.
Thereisnointerconnectionbetweenthewingtanks.
SEATING
The aircraft accommodates 4 adult occupants. Fully
functionalcontrolsallowstheaircrafttobeownfrom
either front seat.
WINTER OPERATIONS
Winter Operations are acceptable with proper oil grades
fortheoperatingtemperatures.Enginepre-heatingis
recommended when the ambient temperature is below
freezing.
Emergency Procedures

Section III
Table of Contents
EMERGENCY AIRSPEEDS 17
ENGINE FAILURE 17
ROUGH RUNNING ENGINE 19
ENGINE FIRE 19
EMERGENCY DESCENT 19
MAXIMUM GLIDE CONFIGURATION 20
LANDING EMERGENCIES 20
SYSTEMS EMERGENCIES 20
Propeller Overspeed
Propeller Damage
Electrical System Failure
 SpeedBrakes
Landing Gear
UNLATCHED DOOR IN FLIGHT 22
SPINS 22
EMERGENCY SPEED REDUCTION 22
NOTE
All airspeeds quoted in this section are indi-
cated airspeeds (KIAS) and assume zero instrument
error. Each aircraft should be calibrated to deter-
mine its specic error for various congurations.
A Pacer method is suggested, ying against a
“known” aircraft.
EMERGENCY AIRSPEEDS
EmergencyDescent(IdlePower,Gear/Flapsup 
      170-274
Best Glide 120
LandingApproach(W/OPower)  110
NOTE
The following check-lists are presented to
capture in a compact format those pilot tasks requir-
ing rapid action. These checklists should be kept
handy for ready access by the pilot, and he should
familiarize him/herself with them before ying the
aircraft. Knowledge of the switches, control, gauge,
etc. location quickly, even blindfolded, is highly
desirable. “Cockpit time” prior to ever ying or
after an absence is time prudently spent. Where
more time would be likely available, rationale will
be added and alternative choices oered. It must
be remembered however that each situation will be
unique in some manner and must be treated as such.
ENGINE FAILURE.
Engine power loss during takeo (not airborne)

SucientRunwayremaining:
Throttle CLOSED
 Brakes  APPLYasnecessary
Stop straight ahead
InsucientRunwayremaining:
Throttle CLOSED
 Brakes  APPLYasnecessary
 Mixture  IDLECUT-OFF
Fuel Selector OFF
Master Switch OFF
 Magneto’s  OFF
Maintain directional control and maneuver to
avoid obstacles.
Engine power loss during takeo (if airborne)
Sucientrunwayremaining:
 Airspeed    100kts.
Maintain directional control and land straight
ahead
Insucientrunwayremaining:
 Airspeed   100kts.
Throttle CLOSED
 Mixture   IDLECUT-OFF
Fuel Selector OFF
Master Switch OFF
 Magneto’s   OFF
Flaps AS REQUIRED
 Maintaindirectionalcontrolandmakeonly
shallow turns to avoid obstacles.
Ifsucientaltitudehasbeengainedtoattemptarestart:
Item Condition
Airspeed 100 KTS
Fuel Selector
 Mixture   RICH
 Magneto’s,Cycle,Then BOTH
 BoostPump(Tocheckforenginedrivenpump
   failure,)HIGH,(momentarily)
 Flaps(onnal)  FULL
In Flight
Establish 110 KIAS glide. Climb to reduce airspeed if
practical,picklandingsite.AttemptAIRSTART.
 CheckFuelSelectortoFullesttank SET
 Mixture    RICH
 BoostPump(Tocheckforenginedrivenpump
   failure,)HIGH,(momentarily)
 Magneto’s,Cycle,ThenBOTH
 Declare(121.5ifnecessary) EMERGENCY
Transponder 7700
NOTE
If power is restored and there is any doubt
as to the cause of the engine stoppage, land at the
nearest airport and determine the cause.

ROUGH RUNNING ENGINE
Item
Condition
Mixture    RICH
 BoostPump(ifabove10,000’) LOW
 Magneto’s,Cycle,Then  BOTH
 Mixture    ADJUST
NOTE
If power is restored and there is any doubt
as to the cause of the engine stoppage, land at the
nearest airport and determine the cause.
ENGINE FIRE
In Flight
DetermineifreisElectrical(acridsmell)ifso:
Avionics Master OFF
Master Switch OFF
All Electrical Equipment OFF
If Fire/smell clears, turn Master switch ON then
each item of equipment one at a time, waiting
lone enough to isolate the cause. If no smell, assume
anunknownsourceandLANDASSOONAS
POSSIBLE AND CORRECT THE PROBLEM.
Ifrecontinues:
Throttle IDLE
 Mixture    CUT-OFF
Fuel Selector OFF
Boost pump OFF
 Landimmediatelyandexittheaircraft
Engine re during start
Starter CONTINUE CRANKING
Mixture IDLECUT-OFF
Throttle FULL OPEN
Boost pump OFF
Fuel Selector OFF
EMERGENCY DECENT
Throttl IDLE
 SpeedBrakes(Ifinstalled) DEPLOY
Propeller HIGH RPM
 Airspeed   170-274
MAXIMUM GLIDE CONFIGURATION
Gear UP
Flaps UP
Propeller
LOW RPM
Airspeed 120
The best glide speed tested to date is 120
KIAS, 1570 FPM resulting in a 7.7:1 glide ratio. Glide
distanceisapproximately0.75NMper1000feetof
altitudeloss,howeverthismayvarysignicantly.It
is suggested that it be established for your individual
aircraft.
LANDING EMERGENCIES
When landing site is selected and you are com-
mittedtolandingoeld,thefollowingchecklistcan
be completed. The use of gear UP versus gear DOWN
is a function of the landing site. If the site is hard and
smooth, a gear DOWN landing should be made, but

if the site is soft or rough a gear UP landing. When
assuredofreachingthelandingsitearea;
Seat Belts/Harness TIGHT
Door seal DEFLATE
Gear AS NEEDED
Boost pump OFF
Fuel Selector OFF
 Mag’s.   OFF
Flaps DOWN
Master OFF
Airspeed DECREASE TO TOUCHDOWN
 Attempttoytheaircraftandkeepthewings
level through the approach and landing until the aircraft
comestorest.Exittheaircraftandremainclearuntil
assuredthereisnopossibilityofre.
SYSTEMS EMERGENCIES
Propeller Overspeed
 Thecontrollablepitchpropellers(withMcCau-
leygovernors)usedontheLancairIVutilizeoilpres-
surefromthegovernortoincreasepitch(lowRPM),
Others may operate in an opposite manner. Therefore it
istheresponsibility;ofthepilottoknowhisaircraftand
its system.
It is however dangerous to run any engine over
its rated rpm and thus the method to reduce any Over-
speed is to immediately reduce the throttle to idle
and reduce airspeed to the point where RPM control is
regained. Slowly add throttle and hold airspeed well
below that at which the overspeed occurred.
Mixturemayneedtobeadjustedforsmoothoperation.
Iftheoverspeedwassignicant,anengineinspection
is called for upon landing. Engine operation for the
balanceoftheight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 construc-
tionvaries,allarehighlystressedandthesenickscause
stress concentrations to a greater or lesser degree which
are dangerous. Refer to the manual for your propeller
for the proper limits of damage, and the proper “care
andfeeding”ofyourpropeller.Preightyouraircraft
accordingly. The loss of any portion of a blade can be
catastrophic.
Electrical System Failure
 Theelectricalsystemofyouraircraftiskeyto
safeoperationintoday’senvironment.Itisrequiredfor
night or IFR operations. If a voltmeter is installed will
beyourkeyindicatorofalternatorfailurewhichthen
places the entire electrical load on the battery.
 Thebatterywillreadapproximately12.4/24.8
voltsonafullcharge,and14+/28+onthealternator.If
youexperiencealternatorfailure;
 CircuitBreakers   CHECK
Master Switch OFF
Avionics Master OFF
Lights OFF
 ThecheckoftheCircuitBreakersmayreveala
poppedbreakerindicatingthesourceofthetrouble.If
so,turnallindividualequipmento,resetthebreaker
andturntheMasterSwitchON.Ifthebreakerdoesnot
pop again, slowly turn various elements of your system
ON one at a time watching for another malfunction,

attempting to isolate the problem.
If you believe the problem has been isolated and you
electtocontinuetheight,remainalertforanother
anomalycausedby;therstdiculty.
Speed Brakes
 IfthespeedbrakesshouldfailintheUP(de-
ployed)position,attempttoretractthembycycling
to full up then down. If electric powered, pull the
circuitbreakerandtheyshouldcollapse.
If all attempts fail to retract them, land with them ful-
lyextendedanduse110KIASonnal.Testinghas
shownthattheLancairhassucientrollcontrolto
safelyywithonespeedbrakeextended,andtheoth-
erfullyretracted,again,nalapproachspeedshould
be 110 KIAS minimum.
Landing Gear
Your Lancair IV gear is held up by hydraulic
pressure.Apressureswitchshutsotheelectrical
powertothepumpwhensystempressure(1100psi)
is achieved. If hydraulic pressure is lost the nose gear
willfreefall,andwiththeaidofagasstrutwilllock
in the down position, the main gear will fall to a ver-
tical position and with the aid of the emergency hand
pumplockintothedownposition.Emergencygear
extensionisaccomplishedasfollows;
Airspeed BELOW 120 KTS
 GearMotorSolenoidCircuitBreaker
PULLED
Gear Handle DOWN
Emergency Hand Pump PUMP
 Thenosegearwillfreefallandit’slightshould
illuminate immediately after lowering the gear handle,
activate the emergency hand pump until the Main Gear
lightsaregreenandthehandleissti.Onceloweredit
is not advisable to attempt a retraction prior to landing
and determining the cause of the failure.
WARNING
Aircraft observers must be used with caution
as not all pilots have the training to safely y “for-
mation” and may not be suciently familiar with
the Lancair gear in its down and locked congura-
tion.
UNLATCHED DOOR IN FLIGHT
 Ifthedoorbecomesunlatchedoropensinight
therst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 has completely
opened do not attempt to close it. Slow the airplane
downtoapproachspeed,extendtheapsandreturnto
the nearest airport and land.
SPINS
Spins are not recommended. If a spin is entered
inadvertentlyorintentionallythestickshouldbeneu-
tralized or placed slightly forward of neutral, the rudder

full against the direction of the spin until rotation is
stopped.Atthispoint,therecoveryshouldbeown
withasmooth,positivepulloutofnomorethan4g’s
takingparticularcarenottoenteranacceleratedstallor
re-enteranotherspin.
WARNING
The Lancairs are aerodynamically very clean
and can lose a lot of altitude in this maneuver.
EMERGENCY SPEED REDUCTION
The nature of this emergency must be consid-
eredbeforeactionistaken,butingeneralthepower
should be reduced to idle, aircraft climbed, speed
brakesdeployed,gearextendedandthemostcritical
wouldbetheextensionofthewingapsbeforereach-
ing132KIAS(Vfe)
Normal Procedures
Section IV
Table of Contents
SAFE OPERATING AIRSPEEDS 24
PREFLIGHTINSPECTION-(Checklist)  24
BEFORESTARTING-(Checklist)   26
STARTING-(Checklist)    26
COLD STARTING 26
FLOODEDENGINE-(Checklist)   27
HOT STARTING 27
BEFORETAKE-OFF-(Checklist)   27
TAKE-OFF&CLIMB-(Checklist)   27
DESCENT-(Checklist)    28
BEFORELANDING-(Checklist)   28
BALKEDLANDING-(Checklist)   28
AFTERLANDING-(Checklist)   28
SECURINGTHEAIRPLANE-(Checklist)  28
LEANING 29
ALTERNATE AIR 31
HEATING&VENTILATION   31
COLD WEATHER OPERATIONS 31
ICING CONDITIONS 32
NOISE 32
SAFE OPERATING AIRSPEEDS
NOTE
All airspeeds in this section are indicated airspeeds