Pa 34 200t Seneca II

SARASOTA FLIGHT INSTRUCTOR.COMSARASOTA FLIGHT INSTRUCTOR.COM

Aircraft Systems Study Series

®

by D. A. Pursell Airline Transport Pilot, CFII, MEI

Copyright 2008

Seneca IIPA34 200T

Disclaimers This guide is based on the Pilot Operating Handbook This guide is based on the Pilot Operating Handbook

for the Piper Seneca model PA34-200T.for the Piper Seneca model PA34-200T.

This guide is for study purposes only, and in no way This guide is for study purposes only, and in no way should be considered a single source of information should be considered a single source of information regarding any flight, system, or emergency operation.regarding any flight, system, or emergency operation.

Images used herein are either original images, or Images used herein are either original images, or obtained from open source files.obtained from open source files.

Use this program along with the actual Pilots Use this program along with the actual Pilots Operating Handbook, your Instructor and your Operating Handbook, your Instructor and your training curriculum.training curriculum.

Section 1Section 1GeneralGeneral

EnginesEngines

EnginesEnginesNumber of enginesNumber of engines 22

Engine TypeEngine Type::Six CylinderSix CylinderDirect DriveDirect DriveHorizontally OpposedHorizontally OpposedFuel InjectedFuel InjectedAir CooledAir CooledTurbo chargedTurbo charged

Engine ManufacturerEngine ManufacturerContinentalContinental

Engine Model Numbers:Engine Model Numbers:LeftLeft TSIO-360E (EB) TSIO-360E (EB) RightRight LTSIO-360E (EB)LTSIO-360E (EB)

ENGINESENGINESRated Horsepower:Rated Horsepower:At sea levelAt sea level 200200Above 12,000 feetAbove 12,000 feet 215215

Rated SpeedRated Speed (rpm) (rpm)25752575

Bore (inches)Bore (inches)4.4384.438

Stroke (inches)Stroke (inches)3.8753.875

Displacement (cubic Inches)Displacement (cubic Inches) 360360Compression RatioCompression Ratio

7.5:17.5:1

PROPELLERSPROPELLERSNumber of PropellersNumber of Propellers 22

Propeller ManufacturerPropeller ManufacturerHartzell or McCauleyHartzell or McCauley

Propeller Type:Propeller Type:Constant SpeedConstant SpeedHydraulically ActuatedHydraulically ActuatedFull FeatheringFull Feathering

Blades:Blades:HartzellHartzell 22McCauleyMcCauley 33

FUELFUELFuel Capacity (U.S. Gal)Fuel Capacity (U.S. Gal)

Without optional tanksWithout optional tanks 9898With optional tanksWith optional tanks 128128

Useable Fuel (U.S. Gal)Useable Fuel (U.S. Gal)Without optional tanksWithout optional tanks 9393With optional tanksWith optional tanks 123123

Minimum Fuel Grade:Minimum Fuel Grade:100 green or 100LL Blue 100 green or 100LL Blue

OilOilOil Capacity (U.S. quarts)Oil Capacity (U.S. quarts) 88Oil SpecificationOil SpecificationPer Continental Service BulletinPer Continental Service Bulletin

Oil Viscosity per ambient temp:Oil Viscosity per ambient temp:Below 40Below 40° F° F SAE No. 30SAE No. 30Above 40Above 40° F° F SAE No. 50SAE No. 50

Minimum for flight is 7 quartsMinimum for flight is 7 quarts

Maximum WeightsMaximum WeightsMax Takeoff Weight:Max Takeoff Weight:4570 lbs.4570 lbs.

Max Landing WeightMax Landing Weight4342 lbs.4342 lbs.

Max Zero Fuel WeightMax Zero Fuel Weight4000 lbs.4000 lbs.

Maximum Weights in Baggage Compartments:Maximum Weights in Baggage Compartments:ForwardForward 100100AftAft 100100

Standard Airplane WeightsStandard Airplane WeightsStandard Empty WeightStandard Empty Weight 28232823

Maximum Useful LoadMaximum Useful Load 17471747

Baggage SpaceBaggage SpaceForward compartment volumeForward compartment volume 15.3 cubic feet15.3 cubic feet

Aft compartment volumeAft compartment volume 24.0 cubic feet24.0 cubic feet

Specific LoadingsSpecific LoadingsWing Loading Wing Loading 22 lbs sq ft22 lbs sq ft

Power Loading Sea LevelPower Loading Sea Level11.4 lbs sq ft11.4 lbs sq ft

Power Loading 12,000 ftPower Loading 12,000 ft10.6 lbs sq ft10.6 lbs sq ft

Section 2Section 2LimitationsLimitations

Airspeed LimitationsAirspeed LimitationsVne Vne Never ExceedNever Exceed

195195

VnoVno Max structural cruiseMax structural cruise163163

VaVa Maneuvering speedManeuvering speedAt 4570 lbsAt 4570 lbs

136136

At 3068 lbsAt 3068 lbs121121

VfeVfe Flaps extendedFlaps extended107107

VmcVmc Minimum Control SpeedMinimum Control Speed 6666

Airspeed LimitationsAirspeed LimitationsVfeVfe Flaps extendedFlaps extended

107107VleVle Maximum gear extendedMaximum gear extended

129129VloVlo Maximum gear “extending”Maximum gear “extending” 129129VloVlo Maximum gear “retraction”Maximum gear “retraction” 107107

Airspeed Indicator MarkingsAirspeed Indicator MarkingsGreen Arc (normal Operating range)Green Arc (normal Operating range)

63 to 16363 to 163Yellow Arc (caution range – smooth air)Yellow Arc (caution range – smooth air)

163 to 195163 to 195White Arc (flaps extended)White Arc (flaps extended)

61 to 10761 to 107Red Radial Line (never exceed)Red Radial Line (never exceed)

195195Red Radial Line (minimum control)Red Radial Line (minimum control)

6666Blue Radial Line (best rate climb single engine)Blue Radial Line (best rate climb single engine)

8989

Power Plant Power Plant LimitationsLimitations

Rated Horsepower at sea levelRated Horsepower at sea level

200200

Rated Horsepower at 12,000 ftRated Horsepower at 12,000 ft

215215

Maximum RPMMaximum RPM

25752575

Maximum Manifold Pressure (inches)Maximum Manifold Pressure (inches)

4040Maximum Cylinder Head Temp.Maximum Cylinder Head Temp.

460460°°

Maximum Oil Temp.Maximum Oil Temp.

240°240°

Power Plant Power Plant LimitationsLimitations

Maximum oil pressureMaximum oil pressure

100 PSI100 PSI

Minimum oil pressureMinimum oil pressure

10 PSI10 PSI

Minimum fuel flowMinimum fuel flow

3.5 PSI3.5 PSI

Maximum fuel flowMaximum fuel flow

20 PSI to 25 GPH 20 PSI to 25 GPH

Power Plant Instrument Power Plant Instrument MarkingsMarkings

Tachometer - Tachometer - Green ArcGreen Arc (normal range) (normal range) 500 rpm to 2575 rpm500 rpm to 2575 rpm

Tachometer - Tachometer - Red LineRed Line (maximum (maximum)) 2575 rpm2575 rpm

Fuel Flow and Pressure:Fuel Flow and Pressure:Green ArcGreen Arc3.5 PSI to 20 PSI3.5 PSI to 20 PSIRed LineRed Line (max) (max)25 GPH (20 PSI)25 GPH (20 PSI)Red LineRed Line (min) (min)3.5 PSI3.5 PSI

Power Plant Instrument Power Plant Instrument MarkingsMarkingsCylinder Head TemperaturesCylinder Head Temperatures

Maximum (Maximum (red linered line) ) 460 460 °°

Normal Range (Normal Range (greengreen arcarc)) 360 360 ° to 460 °° to 460 °

Oil TemperatureOil TemperatureMaximum Maximum 240 °240 °Normal Range (Normal Range (green arcgreen arc))

100 ° to 240 °100 ° to 240 °

Oil PressureOil PressureMaximum Maximum 100 100 PSIPSIMinimum Minimum 10 10 PSIPSICautionCaution 80 to 10080 to 100 PSI PSI

Power Plant Instrument Power Plant Instrument MarkingsMarkingsManifold PressureManifold Pressure

Normal Range (Normal Range (green arcgreen arc))10 to 40 inches HG10 to 40 inches HG

Maximum (Maximum (red linered line))40 inches HG40 inches HG

Exhaust Gas TemperatureExhaust Gas TemperatureRed Line 1650° FRed Line 1650° F

Weight LimitsWeight LimitsMaximum Takeoff WeightMaximum Takeoff Weight

45704570Maximum Landing WeightMaximum Landing Weight

43424342Maximum Weight in Forward BaggageMaximum Weight in Forward Baggage

100100Maximum Weight in Aft BaggageMaximum Weight in Aft Baggage 100100Maximum Zero Fuel WeightMaximum Zero Fuel Weight

40004000

Center of Gravity LimitsCenter of Gravity Limits WeightWeight Forward Limit Forward Limit Aft Limit Aft Limit PoundsPounds Inches Aft of DatumInches Aft of Datum Inches Aft of DatumInches Aft of Datum

34003400 82.082.0 94.694.6

45754575 90.690.6 95.695.6

Note: Datum is 78.4 inches forward of the leading edge from Note: Datum is 78.4 inches forward of the leading edge from the inboard edge of the fuel tank.the inboard edge of the fuel tank.

Maneuver LimitsManeuver LimitsAll intentional Acrobatic All intentional Acrobatic Maneuvers are prohibitedManeuvers are prohibited

Flight Load Factor Limits Flight Load Factor Limits [Flaps UP][Flaps UP]

Positive Load Factor (Max.)Positive Load Factor (Max.)3.8 G3.8 G

Negative Load Factor (Max.)Negative Load Factor (Max.)0.0 G0.0 G

No inverted maneuvers approves.No inverted maneuvers approves.

Types of Operations Types of Operations This plane is equipped in accordance with FAR91 or FAR135 for the This plane is equipped in accordance with FAR91 or FAR135 for the

following operations:following operations:

Day Day VFRVFRNightNight VFRVFRDay Day IFRIFRNightNight IFRIFR

Icing Conditions when equipped per section 2.25 of the pilot Icing Conditions when equipped per section 2.25 of the pilot operations manual.operations manual.

Fuel Limitations Fuel Limitations Un-useable FuelUn-useable Fuel U.S. GallonsU.S. Gallons2.5 gal each wing2.5 gal each wingTotal of 5.0 gallonsTotal of 5.0 gallons

Useable Fuel U.S. GallonsUseable Fuel U.S. Gallons46.5 each wing46.5 each wing Total of 93 Total of 93

(standard tanks)(standard tanks)61.5 each wing61.5 each wing Total of 123 (optional Total of 123 (optional

tanks)tanks)

Gyro Pressure Limitations Gyro Pressure Limitations

Operating Limits for the vacuum pressure:Operating Limits for the vacuum pressure:

4.5 to 5.2 inches Hg for all operations.4.5 to 5.2 inches Hg for all operations.

Flight into known icing Flight into known icing conditionsconditions

The following must be installedThe following must be installed

Pneumatic Wing and Empennage BootsPneumatic Wing and Empennage Boots

Electro-thermal Propeller BootsElectro-thermal Propeller Boots

Electric Windshield PanelElectric Windshield Panel

Heated Pitot HeadHeated Pitot Head

Wing Ice LightWing Ice Light

Heated Lift DetectorsHeated Lift Detectors

Propeller Spinners must be installed.Propeller Spinners must be installed.

Heater LimitationsHeater Limitations

Operation of the combustion heater above 25,000 feet is not Operation of the combustion heater above 25,000 feet is not approved.approved.

Operating Altitude Operating Altitude LimitationsLimitations

Flight above 25,000 feet is not approved.Flight above 25,000 feet is not approved.

Flight up to 25,000 if equipped with supplemental oxygen.Flight up to 25,000 if equipped with supplemental oxygen.

Noise LevelsNoise LevelsThe noise level on this aircraft is as followsThe noise level on this aircraft is as follows

With 2 blade PropellersWith 2 blade Propellers73.5 dB(A)73.5 dB(A)

With 3 blade PropellersWith 3 blade Propellers76.4 dB(A)76.4 dB(A)

Section 3Section 3

Emergency ProceduresEmergency Procedures

Emergency ChecklistsEmergency ChecklistsUse the checklist provided by the Use the checklist provided by the

manufacturer.manufacturer.

Airspeeds for Safe Airspeeds for Safe OperationOperation

Minimum Single Engine ControlMinimum Single Engine Control 66 KIAS66 KIAS

Best Single Engine Rate ClimbBest Single Engine Rate Climb 89 KIAS89 KIAS

Best Single Engine Angle ClimbBest Single Engine Angle Climb 78 KIAS78 KIAS

ManeuveringManeuvering 121 KIAS121 KIAS

Never ExceedNever Exceed 195 KIAS195 KIAS

Engine Inoperative Engine Inoperative ProceduresProcedures

DETECTING DEAD ENGINEDETECTING DEAD ENGINE

Loss of thrustLoss of thrust

Nose will Yaw towards inoperative engineNose will Yaw towards inoperative engine

Engine Failure on Takeoff Below 85 KIAS-Engine Failure on Takeoff Below 85 KIAS-On-RunwayOn-Runway Throttles Throttles Close Both Immediately, Maintain Directional Close Both Immediately, Maintain Directional

ControlControlBrake and Stop Brake and Stop

Airborne with no runway remainingAirborne with no runway remainingThrottlesThrottlesClose Both Immediately, Maintain Directional Close Both Immediately, Maintain Directional

ControlControl

Mixture Mixture Idle Cut-OffIdle Cut-OffFuel SelectorsFuel SelectorsOffOff

Land Land Try to avoid obstructionsTry to avoid obstructions

Engine Failure During Climb/ Engine Failure During Climb/ Speed Below 66 KIASSpeed Below 66 KIAS (Vmc) (Vmc)

RudderRudderApply Towards Operating Engine (Control)Apply Towards Operating Engine (Control)

ThrottlesThrottlesReduce Thrust to Maintain Directional Reduce Thrust to Maintain Directional ControlControl

Pitch AttitudePitch AttitudeLower Nose to Lower Nose to Accelerate to Vyse (89KIASAccelerate to Vyse (89KIAS))

Inoperative EngineInoperative EngineFeather and Secure (Checklist)Feather and Secure (Checklist)

Engine Failure During Climb/Engine Failure During Climb/Speed Above 66 KIASSpeed Above 66 KIAS

RudderRudderMaintain Directional ControlMaintain Directional Control

Pitch AttitudePitch AttitudeAdjust to Accelerate to Vyse (89KIAS)Adjust to Accelerate to Vyse (89KIAS)

Inoperative EngineInoperative EngineFeather and Secure (Checklist)Feather and Secure (Checklist)

Engine Failure During Flight/Engine Failure During Flight/Below 66 KIASBelow 66 KIAS

RudderRudderTowards Operating Engine, Towards Operating Engine, Maintain Directional ControlMaintain Directional Control

ThrottlesThrottlesRetard to prevent yawRetard to prevent yaw

Pitch AttitudePitch AttitudeLower Nose for 66 KIAS+Lower Nose for 66 KIAS+Operating Engine Increase power as speed permits (66 Operating Engine Increase power as speed permits (66

KIAS+)KIAS+) If Altitude PermitsIf Altitude Permits Restart may be attempted (Restart Checklist)Restart may be attempted (Restart Checklist)

If No Restart, or Altitude does not permitIf No Restart, or Altitude does not permit

Inoperative EngineInoperative EngineFeather and Secure (Checklist)Feather and Secure (Checklist)TrimTrimAdj. UP TO 5° Bank toward operating engine (minimal Slip)Adj. UP TO 5° Bank toward operating engine (minimal Slip)Cowl Flap on operating engine as requiredCowl Flap on operating engine as required

Engine Failure During Flight Above 66 Engine Failure During Flight Above 66 KIASKIAS

RudderRudderApply toward operative engineApply toward operative engine

Inop. EngineInop. EngineIdentifyIdentify

Operating EngineOperating EngineAdjust thrust as requiredAdjust thrust as required

Before Securing Inop. Engine---Before Securing Inop. Engine---Fuel Flow - Check (if Low use Aux. Pump HIGH BOOST)Fuel Flow - Check (if Low use Aux. Pump HIGH BOOST)If power is not restored Aux Pump – If power is not restored Aux Pump – OffOffFuel QuantityFuel Quantity CheckCheckFuel Selector (Inop. Engine)Fuel Selector (Inop. Engine) Cross-FeedCross-FeedAlternate AirAlternate Air OnOnMixtureMixture CheckCheckOil Pressure and Temp.Oil Pressure and Temp. CheckCheckMagneto SwitchesMagneto Switches CheckCheckIf Engine Fails to Start proceed to Engine Securing ChecklistIf Engine Fails to Start proceed to Engine Securing Checklist

Engine Failure During Flight Above 66 KIAS Engine Failure During Flight Above 66 KIAS (cont)(cont)

OPERATING ENGINEOPERATING ENGINEPower SettingPower SettingAs requiredAs required

MixtureMixtureAdjust for Power SettingAdjust for Power Setting

Fuel QuantityFuel QuantityCheck for sufficient supplyCheck for sufficient supply

Aux. Fuel PumpAux. Fuel PumpAs RequiredAs Required

Cowl FlapsCowl FlapsAs RequiredAs Required

Electrical LoadElectrical LoadDecrease to minimum loadDecrease to minimum load

LandLandAs soon as possibleAs soon as possible

Engine Securing ChecklistEngine Securing ChecklistTo Attempt to Restore Power before To Attempt to Restore Power before

featheringfeatheringMixturesMixturesAs RequiredAs Required

Fuel SelectorFuel SelectorCross FeedCross Feed

MagnetosMagnetosLeft or Right onlyLeft or Right only

Alternate AirAlternate AirOnOn

Aux. Fuel PumpAux. Fuel PumpUnlatch Unlatch On HIGH if power not restoredOn HIGH if power not restored

Engine Securing Checklist Engine Securing Checklist FEATHERINGFEATHERINGMAINTAIN DIRCETIONAL MAINTAIN DIRCETIONAL

CONTROLCONTROLAND AT LEAST 76 KIASAND AT LEAST 76 KIAS

Mixture ControlsMixture ControlsFull ForwardFull Forward

Propeller ControlsPropeller ControlsFull ForwardFull Forward

Throttle ControlsThrottle ControlsFull Forward (40”Hg Max)Full Forward (40”Hg Max)

FlapsFlapsRetractRetract

GearGearRetractRetract

Engine Securing Checklist Engine Securing Checklist FEATHERINGFEATHERING

Throttle of INOP EngineThrottle of INOP Engine Retard to Verify INOP Retard to Verify INOP

engineengine

Mixture of INOP EngineMixture of INOP Engine Idle Cut-OffIdle Cut-Off

Propeller Control INOP Propeller Control INOP EngineEngine

Feather Before RPM drops Feather Before RPM drops to 800to 800

TrimTrim As RequiredAs Required

Aux. Fuel Pump INOP Aux. Fuel Pump INOP Engine Engine

OFFOFF

Magnetos INOP EngineMagnetos INOP Engine Off Off

Cowl Flaps INOP EngineCowl Flaps INOP Engine CloseClose

Electrical LoadElectrical Load Reduce Reduce

Single Engine LandingSingle Engine Landing

Inoperative EngineInoperative EngineFeather and SecureFeather and Secure

When Landing AssuredWhen Landing AssuredLanding Gear ExtendLanding Gear ExtendWing Flaps Extend to 10°Wing Flaps Extend to 10°Maintain Additional Altitude and speed during Maintain Additional Altitude and speed during

approachapproach

Final Approach SpeedFinal Approach Speed 91 KIAS91 KIAS

Wing FlapsWing FlapsExtend to 25°Extend to 25°

Single Engine Go-AroundSingle Engine Go-Around

MixtureMixtureForwardForward

PropellerPropellerForwardForward

ThrottleThrottleForward Slowly to 40” HgForward Slowly to 40” Hg


Landing GearLanding GearRetractRetract

TO BE AVOIDED IF POSSIBLE

AirspeedAirspeed89 KIAS89 KIAS

TrimTrimSetSet


Air Start (Un-feathering)Air Start (Un-feathering)Fuel Selector INOP EngineFuel Selector INOP EngineOnOn

Aux. Fuel Pump INOP Aux. Fuel Pump INOP EngineEngine

OffOff

ThrottleThrottleOpen ¼ InchOpen ¼ Inch

Propeller ControlPropeller ControlForward to Cruise RPM Pos.Forward to Cruise RPM Pos.

MixtureMixtureRichRich

Magneto SwitchesMagneto SwitchesOnOn

StarterStarterEngage until Prop WindmillsEngage until Prop Windmills

ThrottleThrottleReduce power to warm engineReduce power to warm engine

If Engine does not startIf Engine does not startPrime as requiredPrime as required

Alternator Alternator OnOn

Engine Fire On GroundEngine Fire On GroundENGINE NOT STARTEDENGINE NOT STARTEDMixtureMixtureIdle Cut-OffIdle Cut-Off

ThrottleThrottleOPENOPEN

StarterStarterContinue To Crank engineContinue To Crank engine

ENGINE STARTED

Continue Running to pull fire into manifold

If Fire Continues…

Fuel Selector ValvesOff

MixtureIdle Cut-Off

EVACUATE AIRCRAFT

Engine Fire In FlightEngine Fire In Flight

Fuel Selector (affected Fuel Selector (affected engine)engine)

OffOff

ThrottleThrottle CloseClose

MixtureMixtureIdle Cut-OffIdle Cut-Off

PropellerPropellerFeatherFeather

HeaterHeaterOffOff

DefrosterDefrosterOffOff

LAND AS SOON LAND AS SOON AS POSSIBLEAS POSSIBLE

Fuel Management Single EngineFuel Management Single Engine

Fuel Selector Operating EngineFuel Selector Operating EngineOnOn

Fuel Selector INOP EngineFuel Selector INOP EngineOffOff

Aux. Fuel PumpsAux. Fuel PumpsOffOff

CRUISING---CRUISING---Using Fuel from Tank on same side as Operating EngineUsing Fuel from Tank on same side as Operating Engine

Fuel Management Single EngineFuel Management Single Engine

Fuel Selector Operating EngineFuel Selector Operating EngineCross-FeedCross-Feed



CRUISING---Using Fuel from Tank on side Opposite Operating Engine

Shut Down

Operating

Fuel Management Single Fuel Management Single EngineEngine

Fuel Selector Operating EngineFuel Selector Operating EngineOnOn


LANDING

Fuel Management Single Fuel Management Single EngineEngine

Use Cross-Feed in Level Flight OnlyUse Cross-Feed in Level Flight Only

Do NOT Cross-Feed with Full Fuel on same side as the Operating Do NOT Cross-Feed with Full Fuel on same side as the Operating Engine,Engine,

Vapor Return Fuel will be Vapor Return Fuel will be lostlost though the Vent System though the Vent System

You will be pumping fuel over-boardYou will be pumping fuel over-board

Engine Driven Fuel Pump Engine Driven Fuel Pump FailureFailure

ThrottleRetard

Aux. Fuel PumpUn-Latch

Aux. Fuel PumpOn HI

ThrottleRe-set 75% Power or lower

See Cautions:

Engine Driven Fuel Pump Engine Driven Fuel Pump FailureFailure

CautionsCautionsIf normal engine operation and fuel flow is not immediately re-If normal engine operation and fuel flow is not immediately re-

established, established, Turn OFF Aux. Fuel PumpTurn OFF Aux. Fuel Pump

Lack of fuel flow indications while in the HI position may indicate a leak Lack of fuel flow indications while in the HI position may indicate a leak in the fuel system, or fuel exhaustionin the fuel system, or fuel exhaustion

Do NOT actuate the Aux. Fuel Pump unless vapor suppression is required Do NOT actuate the Aux. Fuel Pump unless vapor suppression is required (LO position) or the engine driven fuel pump fails (HI Position). (LO position) or the engine driven fuel pump fails (HI Position).

The Aux. Fuel Pumps have NO Standby Function.The Aux. Fuel Pumps have NO Standby Function.

Actuation of the HI switch position may when engines are operating may Actuation of the HI switch position may when engines are operating may cause engine roughness and / or Power Loss.cause engine roughness and / or Power Loss.

Landing Gear Unsafe Landing Gear Unsafe WarningWarning

Red LightRed LightGear In TransitGear In Transit

Recycle if Unsafe Gear Indication continuesRecycle if Unsafe Gear Indication continues

Light will illuminate when Gear Horn sounds at Low Power SettingsLight will illuminate when Gear Horn sounds at Low Power Settings

Manual Extension of Landing Manual Extension of Landing GearGear

Check the following before Check the following before extending gear manually:extending gear manually:

Circuit BreakersCircuit BreakersCheckCheck

Master SwitchMaster SwitchOnOn

AlternatorsAlternatorsCheckCheck

Navigation LightsNavigation LightsOff (Daytime)Off (Daytime)


To extend, reposition To extend, reposition clipclip downward clear of downward clear of Emergency Gear Extension Emergency Gear Extension knobknob

Gear SelectorGear SelectorGear Down Locked positionGear Down Locked position

Emergency Gear extend KnobEmergency Gear extend Knob

Pull Pull

Indicator lightsIndicator lights3 Green3 Green

Leave Emergency GearLeave Emergency Gear Extension knob “outExtension knob “out””

Engine Failure in Icing ConditionsEngine Failure in Icing Conditions

Select Alternate Air and attempt restartSelect Alternate Air and attempt restart

In unable to restart engineIn unable to restart engine

INOP EngineINOP EngineSecureSecure

AirspeedAirspeedat or above 89 KIASat or above 89 KIAS

Electrical LoadElectrical LoadReduceReduce

Descend if necessary to maintain airspeedDescend if necessary to maintain airspeed

Avoid Further Icing Conditions if PossibleAvoid Further Icing Conditions if Possible

Land As Soon As PossibleLand As Soon As Possible

Maintain at least 89 KIAS on FinalMaintain at least 89 KIAS on Final

Do Not Lower Gear or Flaps until certain of Do Not Lower Gear or Flaps until certain of landinglanding

Flaps Set to 25°Flaps Set to 25°

Alternator Failure In Icing ConditionsAlternator Failure In Icing Conditions

Over-voltage RelayOver-voltage RelayRe-setRe-set

Circuit BreakersCircuit BreakersCheck and Re-setCheck and Re-set

If unable to restore alternatorIf unable to restore alternator

AvionicsAvionicsAll Off except NAV/COM/TransponderAll Off except NAV/COM/Transponder

Electric WindshieldElectric WindshieldOff to maintain 65 amp loadOff to maintain 65 amp load

If icing continues, terminate flight If icing continues, terminate flight

Prior to landingPrior to landing

Electric WindshieldElectric WindshieldOn if necessaryOn if necessary

Gear may require free-fall Gear may require free-fall extensionextension

Electrical FailuresElectrical Failures

ALT Anunnciator Light illuminatedALT Anunnciator Light illuminatedAmmetersAmmeters Observe to determine INOP Alt.Observe to determine INOP Alt.If both ammeters show zero output, reduce electrical load to min.If both ammeters show zero output, reduce electrical load to min.Turn Off both alt. switches; then turn them On momentarily one at a Turn Off both alt. switches; then turn them On momentarily one at a

time while observing ammeterstime while observing ammetersDetermine Alt. showing Least output and turn it’s switch on.Determine Alt. showing Least output and turn it’s switch on.Electrical LoadsElectrical Loads Re-establish up to 60 AmpsRe-establish up to 60 Amps

If one ammeter shows zero output, cycle switch off-then-onIf one ammeter shows zero output, cycle switch off-then-onIf power is not restored, check breakers and reset once if requiredIf power is not restored, check breakers and reset once if requiredIf alternator remains inoperative, reduce electrical loads and continue If alternator remains inoperative, reduce electrical loads and continue

flightflight

Electrical Failure CautionsElectrical Failure Cautions

Compass error may exceed 10° with both alternators Inoperative.Compass error may exceed 10° with both alternators Inoperative.

Gyro Pressure FailuresGyro Pressure Failures

Pressure Below 4.5 inches HgPressure Below 4.5 inches Hg(Hint….. DON’T TAKEOFF IFR)(Hint….. DON’T TAKEOFF IFR)

RPMRPMIncrease to 2575Increase to 2575

AltitudeAltitudeDescend to maintain 4.5 inches HgDescend to maintain 4.5 inches Hg

Use Electric Turn Indicator to monitor Directional Use Electric Turn Indicator to monitor Directional Gyro and Attitude Indicator Gyro and Attitude Indicator performanceperformance

Combustion Heater Over-heatCombustion Heater Over-heat

Unit will automatically cut-offUnit will automatically cut-off

Do not Attempt to re-start.Do not Attempt to re-start.

SpinsSpins

ThrottlesThrottlesIdleIdle

RudderRudderOpposite direction of spinOpposite direction of spin

Control YokeControl YokeRelease Back PressureRelease Back Pressure

Control YokeControl YokeFull forward if nose does not dropFull forward if nose does not drop

AileronsAileronsNeutralNeutral

Rudder Rudder Neutral after Rotation StopsNeutral after Rotation Stops

Control YokeControl Yoke

Smooth Backpressure to Smooth Backpressure to recover from Diverecover from Dive

Emergency DescentEmergency Descent

ThrottlesThrottlesClosedClosed

PropellersPropellersFull ForwardFull Forward

MixtureMixtureAs RequiredAs Required

Landing GearLanding GearExtendExtend


Section 3Section 3Normal ProceduresNormal Procedures

Before Starting EnginesBefore Starting EnginesSeatsSeatsAdjustedAdjusted

Seat BeltsSeat BeltsOnOn

Parking BrakeParking BrakeOnOn

Circuit BreakersCircuit BreakersInIn

RadiosRadiosOFFOFF

Cowl FlapsCowl FlapsOpenOpen

Alternate AirAlternate AirOffOff

AlternatorsAlternatorsOnOn

Starting EnginesStarting EnginesFuel SelectorFuel SelectorOnOn

MixtureMixtureRichRich

ThrottleThrottle½ Open½ Open



Ignition SwitchesIgnition SwitchesOnOn

PropellerPropellerClearClear

StarterStarterEngageEngage

Primer ButtonPrimer ButtonOn as RequiredOn as Required

ThrottleThrottleRetard when engine startsRetard when engine starts

Oil PressureOil PressureCheckCheck

Repeat for Opposite EngineRepeat for Opposite Engine

AlternatorsAlternatorsCheckCheck

Gyro PressureGyro PressureCheckCheck

Starting Engines when FloodedStarting Engines when FloodedMixtureMixtureIdle Cut-OffIdle Cut-Off

ThrottleThrottleFull ForwardFull Forward



Ignition SwitchIgnition SwitchOnOn

Aux. Fuel PumpAux. Fuel PumpOffOff

PropellerPropellerClearClear

When Engine Starts:When Engine Starts:

ThrottleThrottle RetardRetard

MixtureMixtureAdvance SlowlyAdvance Slowly

Starting Engines-External PowerStarting Engines-External PowerMaster SwitchMaster SwitchOffOff

All Electrical EquipmentAll Electrical EquipmentOffOff

TerminalsTerminalsConnectConnect

External Power PlugExternal Power PlugInsert into receptacleInsert into receptacle

Proceed with Normal Start ProceduresProceed with Normal Start Procedures

ThrottlesThrottlesLowest Possible RPMLowest Possible RPM

External Power PlugExternal Power PlugDisconnectDisconnect

Master SwitchMaster Switch On-Check AmmeterOn-Check Ammeter

Oil PressureOil PressureCheckCheck

Warm UpWarm UpThrottlesThrottles1,000 to 1,200 RPM1,000 to 1,200 RPM

TaxiingTaxiingChocksChocksRemoveRemove

Taxi AreaTaxi AreaClearClear

ThrottleThrottleApply SlowlyApply Slowly

BrakesBrakesCheckCheck

SteeringSteeringCheckCheck

InstrumentsInstrumentsCheckCheck

Heater and defrosterHeater and defrosterCheckCheck

Fuel SelectorFuel SelectorON, Check Cross-FeedON, Check Cross-Feed

AutopilotAutopilotOffOff

Before Takeoff – Ground Check Before Takeoff – Ground Check (part 1)(part 1)Parking brakeParking brake

SetSet

Mixture ControlsMixture ControlsForwardForward

Propeller ControlsPropeller ControlsForwardForward

Throttle ControlsThrottle Controls1000 RPM1000 RPM

Manifold Pressure LinesManifold Pressure LinesDrainDrain

Propeller ControlsPropeller ControlsCheck Feathering Check Feathering

300 RPM Max. Drop300 RPM Max. Drop

Throttle ControlsThrottle Controls1900 RPM1900 RPM

Propeller ControlsPropeller ControlsCheck GovernorCheck Governor


Alternate AirAlternate AirOn, then OffOn, then Off

MagnetosMagnetosCheck, Max. Drop 150 RPM Check, Max. Drop 150 RPM

Max. Differential 50 RPMMax. Differential 50 RPM

Before Takeoff – Ground Check Before Takeoff – Ground Check (part 2)(part 2)Alternator OutputAlternator Output

CheckCheck

Gyro PressureGyro Pressure4.5 to 5.2 inches Hg4.5 to 5.2 inches Hg

ThrottlesThrottles800 to 1000 RPM800 to 1000 RPM

Fuel SelectorsFuel SelectorsOnOn

AlternatorsAlternatorsOnOn

Engine GaugesEngine GaugesIn the GreenIn the Green

AltimeterAltimeterSetSet

Attitude IndicatorAttitude Indicator

SetSet

Directional GyroDirectional GyroSetSet

ClockClock SetSet

MixturesMixturesSetSet

PropellersPropellersSet – Full ForwardSet – Full Forward

Before Takeoff – Ground Check Before Takeoff – Ground Check (part 3)(part 3)

Quadrant frictionQuadrant frictionSetSet

Alternate AirAlternate AirOffOff

SeatbacksSeatbacksErectErect

Wing FlapsWing FlapsSetSet

TrimTrimSetSet

Seat BeltsSeat Belts OnOn

ControlsControlsFree – Full TravelFree – Full Travel

DoorsDoorsLatchedLatched


Pitot HeatPitot HeatAs RequiredAs Required

Takeoff CautionsTakeoff CautionsDo not exceed 40 inches Manifold Pressure.Do not exceed 40 inches Manifold Pressure.

Fast Taxi turns immediately prior to takeoff run can cause Fast Taxi turns immediately prior to takeoff run can cause temporary malfunction of one engine during takeoff.temporary malfunction of one engine during takeoff.

Normal sea level takeoff at 39” Hg and 2575 RPM.Normal sea level takeoff at 39” Hg and 2575 RPM.

Adjust mixture prior to takeoff for High Elevation Airports.Adjust mixture prior to takeoff for High Elevation Airports.

DO NOT EXCEED 40” Hg Manifold Pressure DO NOT EXCEED 40” Hg Manifold Pressure

Normal Takeoff (Flaps Up)Normal Takeoff (Flaps Up)On RunwayOn Runway

StrobesStrobes OnOn

TransponderTransponderOnOn

Landing LightLanding Light OnOn

FlapsFlapsUpUp

Stabilator TrimStabilator TrimTakeoff RangeTakeoff Range

PowerPowerApply full throttle 39” HgApply full throttle 39” Hg

Accelerate toAccelerate to 66-71 KIAS66-71 KIAS

Ease back Control Yoke to Climb Ease back Control Yoke to Climb AttitudeAttitude

After Lift-Off Accelerate to After Lift-Off Accelerate to 89 KIAS (Vyse)89 KIAS (Vyse)

GearGear UpUp

Short Field Takeoff (Flaps Up)Short Field Takeoff (Flaps Up)On RunwayOn Runway

StrobesStrobes OnOn



FlapsFlapsUpUp


BrakesBrakesSetSet

PowerPowerApply full throttle 39” HgApply full throttle 39” Hg

BrakesBrakesReleaseRelease

Accelerate toAccelerate to 66 KIAS66 KIASRotate and Trim to 71 KIAS through 50 ftRotate and Trim to 71 KIAS through 50 ft

Obstruction ClearanceObstruction ClearanceAccelerate to 79 KIASAccelerate to 79 KIAS

No ObstructionNo ObstructionAccelerate to 89 KIASAccelerate to 89 KIAS

GearGear UpUp

Short Field Takeoff (Flaps 25Short Field Takeoff (Flaps 25°°))On RunwayOn Runway

StrobesStrobes OnOn


StrobesStrobesOnOn


FlapsFlaps25°25°


BrakesSet

PowerApply full throttle 39” Hg

BrakesRelease

Accelerate to 61 KIASRotate to 69 KIAS through 50 ft

Obstruction ClearanceAccelerate to 79 KIAS

No ObstructionAccelerate to 89 KIAS

Gear Up

Takeoff Climb Takeoff Climb MixtureMixture

Full RichFull Rich

Propeller SpeedPropeller Speed

2575 RPM2575 RPM

Manifold PressureManifold Pressure40 inches Hg Max.40 inches Hg Max.

Climb SpeedsClimb SpeedsBest AngleBest Angle76 KIAS76 KIAS

Best RateBest Rate89 KIAS89 KIAS

Cowl FlapsCowl Flaps

As requiredAs required

Cruise ClimbCruise ClimbMixtureMixtureFull RichFull Rich

Prop SpeedProp Speed2450 RPM2450 RPM

Manifold PressureManifold Pressure31.5 inches Hg31.5 inches Hg

Climb SpeedClimb Speed102 KIAS102 KIAS

Cowl FlapsCowl FlapsAs requiredAs required

CruisingCruising

Power

Set

Cowl FlapsAs Required

Mixture

Adjust

Engine Gauges

Monitor

Refer to Performance Charts for Power SettingsRefer to Performance Charts for Power Settings

DescentDescentMixturesMixturesEnrich with descentEnrich with descent

ThrottlesThrottlesCruise SettingCruise Setting

Cowl FlapsCowl FlapsCLOSEDCLOSED

Approach and Landing (part 1)Approach and Landing (part 1)Gear Warning HornGear Warning HornCheckCheck

AirspeedAirspeed98 KIAS downwind98 KIAS downwind

Seat backsSeat backsErectErect

Seat BeltsSeat BeltsOnOn

Fuel SelectorsFuel SelectorsOnOn



Mixture ControlsMixture ControlsSetSet

PropellersPropellersSetSet

Landing GearLanding GearDown – 129 KIASDown – 129 KIASFlapsFlaps

Set as RequiredSet as Required

Approach and Landing (part 2)Approach and Landing (part 2)Base LegBase Leg97 KIAS97 KIASFinalFinal87 KIAS87 KIAS

Close FinalClose FinalPowerPower ReduceReduce


Go AroundGo Around

Full Takeoff PowerFull Takeoff Power40” Hg Max.40” Hg Max.


GearGearUpUp

Cowl FlapsCowl FlapsAdjustAdjust

After LandingAfter LandingClear of RunwayClear of Runway

TransponderTransponderOffOffStrobesStrobes OffOffLanding LightLanding LightOffOffRadiosRadios SetSetFlapsFlapsUpUpCowl FlapsCowl FlapsFull OpenFull OpenAlternate AirAlternate AirOffOff

ShutdownShutdownHeaterHeaterFan 2 min. then offFan 2 min. then off

Radio and Electrical EquipmentRadio and Electrical EquipmentOffOff

Mixture ControlsMixture ControlsIdle-Cut-OffIdle-Cut-Off

Magnetos SwitchesMagnetos SwitchesOffOff

Master SwitchMaster SwitchOffOff

Parking BrakesParking BrakesSet as RequiredSet as Required

Section 7Section 7SYSTEMS SYSTEMS

Description and OperationDescription and Operation

The AirplaneThe AirplaneAirframe is constructed with Aluminum AlloyAirframe is constructed with Aluminum Alloy

Exceptions are landing-gear struts, cowling bowls, nose-cone, and Exceptions are landing-gear struts, cowling bowls, nose-cone, and ABS plastic components on the tail, wingtips, rudder and stabilator ABS plastic components on the tail, wingtips, rudder and stabilator

Fuselage is semi-monocoque in designFuselage is semi-monocoque in design

Front-door on the right and a rear door on the left, with a cargo door Front-door on the right and a rear door on the left, with a cargo door installed aft of the rear doorinstalled aft of the rear door

A door on the nose section provides access to the forward baggage A door on the nose section provides access to the forward baggage storagestorage

The AirplaneThe Airplane

Wing is conventional designWing is conventional design

Laminar flow NACA 65 2 – 415Laminar flow NACA 65 2 – 415

The 4-position wing flaps are mechanically operated by a The 4-position wing flaps are mechanically operated by a handle located between the front seatshandle located between the front seats

Each wing contains 2 fuel tanks (optional 3Each wing contains 2 fuel tanks (optional 3rdrd) and are filled by ) and are filled by a single filler neck located outboard of each engine nacellea single filler neck located outboard of each engine nacelle

The AirplaneThe AirplaneThe Empennage is made up of the following: A vertical The Empennage is made up of the following: A vertical

Stabilizer, an all-moveable horizontal stabilator, and a Stabilizer, an all-moveable horizontal stabilator, and a rudderrudder

The stabilator incorporates an anit-servo trim-tab which The stabilator incorporates an anit-servo trim-tab which improves longitudinal stability, and provides longitudinal improves longitudinal stability, and provides longitudinal trimtrim

This tab moves in the same direction as the stabilator, but This tab moves in the same direction as the stabilator, but with increased travelwith increased travel

Rudder effectiveness is increased by an anti-servo tab on the Rudder effectiveness is increased by an anti-servo tab on the rudderrudder

The EnginesThe Engines

The Seneca II is powered by 2 Teledyne Continental The Seneca II is powered by 2 Teledyne Continental Six-cylinder turbo-charged engines rated at 200 hp Six-cylinder turbo-charged engines rated at 200 hp at 2750 RPM at sea levelat 2750 RPM at sea level

The engines are air-cooled, fuel injected, and are The engines are air-cooled, fuel injected, and are equipped with oil coolers, a low temperature equipped with oil coolers, a low temperature bypass system, and engine mounted oil filtersbypass system, and engine mounted oil filters

Asymmetric Thrust during takeoff is and climb is Asymmetric Thrust during takeoff is and climb is eliminated by counter-rotation of the engines with eliminated by counter-rotation of the engines with the left rotating clockwise, and the right rotating the left rotating clockwise, and the right rotating counter-clockwisecounter-clockwise

The EnginesThe EnginesRay-Jay turbo-chargers on each engine are powered by exhaust Ray-Jay turbo-chargers on each engine are powered by exhaust

gases.gases.Exhaust gases rotate a turbine wheel, which in turn drives an air Exhaust gases rotate a turbine wheel, which in turn drives an air

compressorcompressorInduction Air is compressed and distributed into the engine air Induction Air is compressed and distributed into the engine air

manifold, and the exhaust gases which drive the compressor are manifold, and the exhaust gases which drive the compressor are discharged overboarddischarged overboard

Engine induction air is taken from within the cowling, filtered, then Engine induction air is taken from within the cowling, filtered, then directed to the compressor inletdirected to the compressor inlet

Each cylinder is supplied with pressurized air in operations to Each cylinder is supplied with pressurized air in operations to maximum altitudemaximum altitude

A pressure relief valve protects the engines from exceeding 42”HgA pressure relief valve protects the engines from exceeding 42”HgTurbo by-pass orifice is set for 40” Hg at 12,000 Dens. Alt at full pwrTurbo by-pass orifice is set for 40” Hg at 12,000 Dens. Alt at full pwr

The EnginesThe EnginesIntake air-box incorporates a manually operated 2way valve Intake air-box incorporates a manually operated 2way valve

designed to allow induction air to either pass into the designed to allow induction air to either pass into the compressor through the filter or to bypass the filter and compressor through the filter or to bypass the filter and supply heated air directly to the turbochargersupply heated air directly to the turbocharger

There is a suck-in-door which opens in the event the primary air There is a suck-in-door which opens in the event the primary air source becomes blockedsource becomes blocked

Alternate-Air selection assures induction air flow should the Alternate-Air selection assures induction air flow should the primary air source become blockedprimary air source become blocked

This air is heated an thus protects against blockage due to snow This air is heated an thus protects against blockage due to snow or freezing rainor freezing rain

Alternate is un-filtered and should not be used during ground Alternate is un-filtered and should not be used during ground operations operations

Primary air should always be used during takeoffPrimary air should always be used during takeoff

The EnginesThe EnginesThe Fuel injection system is a “continuous flow” typeThe Fuel injection system is a “continuous flow” type

The system incorporates metering which measures the rate at which The system incorporates metering which measures the rate at which turbo-charged air is being used by the engine and dispenses fuel turbo-charged air is being used by the engine and dispenses fuel to the cylinders proportionallyto the cylinders proportionally

Fuel is supplied to the injector pump at a greater rate than the Fuel is supplied to the injector pump at a greater rate than the engine requiresengine requires

The EnginesThe EnginesEngine Controls consist of individual Throttles, Propeller Engine Controls consist of individual Throttles, Propeller

Controls, and Mixture controls for each engineControls, and Mixture controls for each engine

Engine controls are located on the control quadrant on the Engine controls are located on the control quadrant on the lower center of the instrument panellower center of the instrument panel

The controls use teflon-lined control cables to reduce friction The controls use teflon-lined control cables to reduce friction and bindingand binding

Throttles are used to control manifold pressure an incorporate Throttles are used to control manifold pressure an incorporate a gear-up warning switch that is activated when the a gear-up warning switch that is activated when the throttles are closed and the landing gear is not downthrottles are closed and the landing gear is not down

The EnginesThe EnginesThe Propeller Control levers are used to adjust the propeller The Propeller Control levers are used to adjust the propeller

speed form high RPM to Featherspeed form high RPM to Feather

The Mixture Control levers are used to adjust the air-to-fuel The Mixture Control levers are used to adjust the air-to-fuel ratioratio

An engine is shut-down by placing the mixture control in the An engine is shut-down by placing the mixture control in the full lean (idle-cut-off) positionfull lean (idle-cut-off) position

Alternate air controls are located on the control quadrant just Alternate air controls are located on the control quadrant just below the engine control leversbelow the engine control levers

Alternate air OFF (up) provides normal filtered airAlternate air OFF (up) provides normal filtered airAlternate air ON (down) provides unfiltered, heated airAlternate air ON (down) provides unfiltered, heated air

The EnginesThe EnginesCowl flap controls are located just below the control Cowl flap controls are located just below the control

quadrant and have three positions… full open, full quadrant and have three positions… full open, full closed, and intermediateclosed, and intermediate

The cowl flap controls lock in each selected position The cowl flap controls lock in each selected position The lock must be depressed to move to another The lock must be depressed to move to another

positionposition

ALL THROTTLE OPERATIONS SHOULD BE MADE WITH ALL THROTTLE OPERATIONS SHOULD BE MADE WITH SMOOTH NOT-TO-RAPID MOVEMENTS TO PREVENT SMOOTH NOT-TO-RAPID MOVEMENTS TO PREVENT UNECESSARY WEAR OR DAMAGE TO THE ENGINE, UNECESSARY WEAR OR DAMAGE TO THE ENGINE, AND TO ALLOW TIME FOR THE TURBO-CHARGER AND TO ALLOW TIME FOR THE TURBO-CHARGER SPEED TO STABILIZESPEED TO STABILIZE

The PropellersThe PropellersCounter-rotating propellers provide balance thrust during takeoff Counter-rotating propellers provide balance thrust during takeoff

and climb and eliminate the “critical engine” factor in single-and climb and eliminate the “critical engine” factor in single-engine flightengine flight

Two-blade, constant-speed, controllable pitch, feathering Hartzell Two-blade, constant-speed, controllable pitch, feathering Hartzell propellers are standard equipmentpropellers are standard equipment

Pitch is controlled by oil and nitrogen pressurePitch is controlled by oil and nitrogen pressure

Oil pressure sends the a propeller toward the high RPM/un-Oil pressure sends the a propeller toward the high RPM/un-feathered position,feathered position,

Nitrogen sends the propeller toward the Low RPM/Feather Nitrogen sends the propeller toward the Low RPM/Feather position, and prevents over-speedingposition, and prevents over-speeding

Governors on each engine supply engine oil at various pressures Governors on each engine supply engine oil at various pressures through the propeller shafts to maintain constant RPM settingsthrough the propeller shafts to maintain constant RPM settings

The PropellersThe PropellersFeathering of a propeller is done by moving the control lever Feathering of a propeller is done by moving the control lever

to the Completely through Low-RPM, Feather positionto the Completely through Low-RPM, Feather positionFeathering takes place in approximately six secondsFeathering takes place in approximately six seconds

Un-feathering is accomplished by moving the propeller control Un-feathering is accomplished by moving the propeller control lever forward and engaging the starter until the propeller is lever forward and engaging the starter until the propeller is wind-millingwind-milling

A feathering lock (operated by centrifugal force) prevents A feathering lock (operated by centrifugal force) prevents feathering during engine shut-down by making it impossible feathering during engine shut-down by making it impossible to feather if engine speed drops below 800 RPMto feather if engine speed drops below 800 RPM

For this reason, when feathering is desired or necessary, it For this reason, when feathering is desired or necessary, it must be done before the engine falls below 800 RPMmust be done before the engine falls below 800 RPM

Landing GearLanding Gear The Seneca II is equipped with hydraulically operated, fully The Seneca II is equipped with hydraulically operated, fully

retractable, tricycle landing gearretractable, tricycle landing gear

Hydraulic pressure for gear operation is furnished by an Hydraulic pressure for gear operation is furnished by an electrically powered, reversible hydraulic pumpelectrically powered, reversible hydraulic pump

The Pump is activated by a two-position gear selector The Pump is activated by a two-position gear selector switch located to the left of the control quadrant on the switch located to the left of the control quadrant on the instrument panelinstrument panel

CAUTIONCAUTION If the landing gear is in transit and the hydraulic pump is If the landing gear is in transit and the hydraulic pump is

running it is NOT advisable to move the gear selector running it is NOT advisable to move the gear selector switch to the opposite position before the gear has switch to the opposite position before the gear has reached its full travel limit, because sudden reversal may reached its full travel limit, because sudden reversal may damage the electric pumpdamage the electric pump

Landing GearLanding GearThe landing gear is designed to extend without the hydraulic The landing gear is designed to extend without the hydraulic

pumppump

The gear is held “up” by hydraulic pressureThe gear is held “up” by hydraulic pressure

If the hydraulic system fails for any reason, gravity will allow If the hydraulic system fails for any reason, gravity will allow the gear to extendthe gear to extend

On retraction, the mains retract inboard into the wings, and On retraction, the mains retract inboard into the wings, and the nose-wheel retracts forward into the nosethe nose-wheel retracts forward into the nose

Aerodynamic loads and springs assist in gear extension and in Aerodynamic loads and springs assist in gear extension and in locking the gear in the down positionlocking the gear in the down position

Landing GearLanding Gear

Landing Gear HydraulicsLanding Gear Hydraulics

Landing GearLanding GearTo extend the landing gear in the event of hydraulic failure it To extend the landing gear in the event of hydraulic failure it

is only necessary to only relieve the hydraulic pressure.is only necessary to only relieve the hydraulic pressure.

Emergency gear extension must not be attempted at Emergency gear extension must not be attempted at airspeeds in excess of 84 knotsairspeeds in excess of 84 knots

An emergency gear extension knob is located directly beneath An emergency gear extension knob is located directly beneath the landing gear extension handle for this purposethe landing gear extension handle for this purpose

Pulling this knob releases hydraulic pressure and allows the Pulling this knob releases hydraulic pressure and allows the landing landing

The knob is guarded by a spring retainer that The knob is guarded by a spring retainer that mustmust be be disengaged before pulling the knobdisengaged before pulling the knob

Landing GearLanding Gear

Landing Gear Selector and Landing Gear Selector and Emergency ReleaseEmergency Release

Landing GearLanding Gear When the gear is fully extended or retracted, and the gear When the gear is fully extended or retracted, and the gear

selector is in the corresponding position, electrical limit selector is in the corresponding position, electrical limit switches stop the flow of current to the hydraulic pumpswitches stop the flow of current to the hydraulic pump

Lights directly above the Landing gear selector illuminate to Lights directly above the Landing gear selector illuminate to indicate that all three landing gear are down and lockedindicate that all three landing gear are down and locked

If the gear is neither fully up or fully down a If the gear is neither fully up or fully down a redred warning warning light on the instrument panel illuminateslight on the instrument panel illuminates

Should the throttles be placed in a low setting (landing) Should the throttles be placed in a low setting (landing) while the gear is in retracted, a warning horn sounds to while the gear is in retracted, a warning horn sounds to alert the pilot that the gear is retracted.alert the pilot that the gear is retracted.

The horn emits a 90 cycles per minute beeping soundThe horn emits a 90 cycles per minute beeping sound

Landing GearLanding Gear If one or two of the three green lights do not illuminate when If one or two of the three green lights do not illuminate when

the gear-down position is selected, any of the following the gear-down position is selected, any of the following conditions may exist:conditions may exist:

-Gear not locked down-Gear not locked down -Bulb is burned out-Bulb is burned out -There is a malfunction in the indicating system-There is a malfunction in the indicating system

A micro switch incorporated in the throttle quadrant A micro switch incorporated in the throttle quadrant activates the gear warning horn under the following activates the gear warning horn under the following conditions:conditions:

Gear not locked down and manifold pressure less than 14” Gear not locked down and manifold pressure less than 14” HgHg

The gear selector switch is in the UP position when the The gear selector switch is in the UP position when the airplane is on the groundairplane is on the ground

Landing GearLanding Gear To prevent accidental gear retraction should the gear selector be To prevent accidental gear retraction should the gear selector be

placed in the UP position while on the ground a SQUAT switch placed in the UP position while on the ground a SQUAT switch located on the left main landing gear will prevent the hydraulic located on the left main landing gear will prevent the hydraulic pump from actuating if the master switch is turned on.pump from actuating if the master switch is turned on.

On takeoff, the main oleo strut drops to full extension, and the On takeoff, the main oleo strut drops to full extension, and the safety switch closes to complete the circuit to allow pump safety switch closes to complete the circuit to allow pump operationoperation

During pre-flight be sure the landing gear selector is in the DOWN During pre-flight be sure the landing gear selector is in the DOWN position and that 3 green lights are illuminatedposition and that 3 green lights are illuminated

On takeoff the gear should be retracted BEFORE reaching 107 KTSOn takeoff the gear should be retracted BEFORE reaching 107 KTS The Landing gear may be extended at any speed below 129 KTSThe Landing gear may be extended at any speed below 129 KTS

Brake SystemBrake System The brake system is designed to meet all normal braking The brake system is designed to meet all normal braking

needsneeds

2 single-disc, double-puck brake assemblies mounted on 2 single-disc, double-puck brake assemblies mounted on each main gear are actuated by toe-brake pedals mounted each main gear are actuated by toe-brake pedals mounted on both pilots rudder pedals, or by the hand operated brake on both pilots rudder pedals, or by the hand operated brake level located below and behind the left center of the level located below and behind the left center of the instrument panelinstrument panel

The parking brake is engaged by pulling the brake handle The parking brake is engaged by pulling the brake handle and depressing the button on the left of the handleand depressing the button on the left of the handle

The brake is released by pulling on the brake handle and The brake is released by pulling on the brake handle and releasingreleasing

Flight Control SystemFlight Control System Dual flight controls are installed in the Seneca II as a Dual flight controls are installed in the Seneca II as a

standardstandard The controls actuate the flight control surfaces through The controls actuate the flight control surfaces through

a cable systema cable system The stabilator is an all-moveable slab type, with an anti-The stabilator is an all-moveable slab type, with an anti-

servo trim tab mounted on the trailing edge. This Tab is servo trim tab mounted on the trailing edge. This Tab is actuated by a control wheel mounted between the seatsactuated by a control wheel mounted between the seats

Ailerons are “Frise” type and allows the leading edge of Ailerons are “Frise” type and allows the leading edge of the airleron to extent into the air-stream to provide the airleron to extent into the air-stream to provide increased drag and improved roll controlincreased drag and improved roll control

The vertical tail surface is fitted with a rudder which The vertical tail surface is fitted with a rudder which incorporates a rudder-trim tab. The rudder-trim control incorporates a rudder-trim tab. The rudder-trim control is located on the control console between the front is located on the control console between the front seatsseats

Flight Control SystemFlight Control System Flaps are manually operated and spring loaded to return to Flaps are manually operated and spring loaded to return to

the retracted positionthe retracted position A four-position flap control lever between the front seats A four-position flap control lever between the front seats

adjusts the flaps for reduced landing speeds and glide path adjusts the flaps for reduced landing speeds and glide path controlcontrol

The flaps have three extension settings:The flaps have three extension settings: 10 degrees10 degrees 25 degrees25 degrees 40 degrees40 degrees A button on the end of the lever must be pressed before A button on the end of the lever must be pressed before

the control can be movedthe control can be moved

Fuel SystemFuel System Fuel is stored in fuel tanks located in each wing. Fuel is stored in fuel tanks located in each wing. The tanks in each wing are interconnected to act as a single The tanks in each wing are interconnected to act as a single

tank.tank. All tanks on each wing are fueled through a port located All tanks on each wing are fueled through a port located

outboard of the engine nacelle.outboard of the engine nacelle. Fuel is consumed from the in-board tanks (refilled from Fuel is consumed from the in-board tanks (refilled from

outboards)outboards) 2.5 Gallons in each wing is un-useable.2.5 Gallons in each wing is un-useable. Minimum fuel grade is 100 LL blue or 100 aviation grade Minimum fuel grade is 100 LL blue or 100 aviation grade

green.green. Fuel Tank Vents located under each wing are of a non-icing Fuel Tank Vents located under each wing are of a non-icing

design.design.

Fuel SystemFuel System The Fuel-Injection system is a “Continuous Flow” type.The Fuel-Injection system is a “Continuous Flow” type.

The system uses a vapor-return line leading back to the fuel The system uses a vapor-return line leading back to the fuel tanks.tanks.

This allows vapor laden fuel to be returned to the tanks.This allows vapor laden fuel to be returned to the tanks.

Each engine has an engine driven fuel pump that is a part of Each engine has an engine driven fuel pump that is a part of the fuel injection system.the fuel injection system.

Fuel SystemFuel System An Auxiliary Fuel System is provided.An Auxiliary Fuel System is provided. The Electric powered Auxiliary fuel system supplies fuel to The Electric powered Auxiliary fuel system supplies fuel to

the engine in the event of engine-driven fuel pump shaft the engine in the event of engine-driven fuel pump shaft failure or malfunction.failure or malfunction.

The system is also used for ground and in-flight starting The system is also used for ground and in-flight starting and for vapor suppression.and for vapor suppression.

The 2 Aux. Fuel pumps switches are located on the The 2 Aux. Fuel pumps switches are located on the Electrical Side panel and are 3-position rocker-switches; LO, Electrical Side panel and are 3-position rocker-switches; LO, HI. And OFF.HI. And OFF.

Fuel SystemFuel System HI Aux. Fuel Pressure is selected by pushing the Bottom of the HI Aux. Fuel Pressure is selected by pushing the Bottom of the

switch. This can only be done AFTER unlatching the Guard.switch. This can only be done AFTER unlatching the Guard. When HI is selected, an Amber Light illuminates near the When HI is selected, an Amber Light illuminates near the

annunciation panel. annunciation panel. The lights dim whenever pump pressure reduces automatically The lights dim whenever pump pressure reduces automatically

and manifold pressure is approximately below 21” Hg.and manifold pressure is approximately below 21” Hg. In case of engine driven pump failure, auxiliary fuel pressure In case of engine driven pump failure, auxiliary fuel pressure

should be selected.should be selected. Adequate flow is provided for 75% Adequate flow is provided for 75% Manual leaning is required at altitudes above 15,000 ft, and for Manual leaning is required at altitudes above 15,000 ft, and for

engine speeds less than 2,300 RPM.engine speeds less than 2,300 RPM. An Hg manifold pressure switch will select lower fuel pressure An Hg manifold pressure switch will select lower fuel pressure

when the throttle is reduced below 21” Hg, and the HI Aux fuel when the throttle is reduced below 21” Hg, and the HI Aux fuel pump is on.pump is on.

Fuel SystemFuel System NOTE:NOTE:

Excessive Fuel pressure and a very rich mixture will occur if Excessive Fuel pressure and a very rich mixture will occur if the HI position is selected when the engine fuel system is the HI position is selected when the engine fuel system is operating normally.operating normally.

Low auxiliary fuel pressure is available and may be used Low auxiliary fuel pressure is available and may be used during normal engine operation on the ground and in flight for during normal engine operation on the ground and in flight for vapor suppression should it be necessary.vapor suppression should it be necessary.

Indications of excessive fuel vapor are:Indications of excessive fuel vapor are: Unstable Engine OperationsUnstable Engine Operations Fluctuating Fuel Flow Indications during idle or at high Fluctuating Fuel Flow Indications during idle or at high

altitudes.altitudes. Separate spring-loaded OFF primer button switches (adjacent Separate spring-loaded OFF primer button switches (adjacent

to the starter switches) are used to select HI Aux fuel pump to the starter switches) are used to select HI Aux fuel pump operations for priming the engines. These may be used for operations for priming the engines. These may be used for hot and cold engine starts.hot and cold engine starts.

Fuel System ManagementFuel System Management

The controls for management of the system are located between the The controls for management of the system are located between the front seats.front seats.

There is a control lever for each engine labeled ON, OFF, X-FEED.There is a control lever for each engine labeled ON, OFF, X-FEED. Normal operations the selector position is ON.Normal operations the selector position is ON. Each engine draws fuel from the wing tanks next to it.Each engine draws fuel from the wing tanks next to it. The fuel systems for both engines are interconnected by cross-feed The fuel systems for both engines are interconnected by cross-feed

lines.lines. With X-FEED selected the engine is drawing fuel from the wing tank With X-FEED selected the engine is drawing fuel from the wing tank

on the opposite side.on the opposite side. This allows extended range with 1 engine inoperative, and provides a This allows extended range with 1 engine inoperative, and provides a

balance control.balance control. OFF shuts the fuel flow off for the engine selected.OFF shuts the fuel flow off for the engine selected. DO NOT OPERATE with x-feed selected on both engines.DO NOT OPERATE with x-feed selected on both engines. DO NOT TAKEOFF with x-feed selected.DO NOT TAKEOFF with x-feed selected.

Fuel System ManagementFuel System Management

Before each flight, fuel must be drained low points in the system to ensure Before each flight, fuel must be drained low points in the system to ensure any accumulation of moisture or sediment is removed from the system.any accumulation of moisture or sediment is removed from the system.

Fuel Drains are provided for this purpose and are located….Fuel Drains are provided for this purpose and are located…. Each Fuel Filter (2)Each Fuel Filter (2) Each Fuel Tank (4)Each Fuel Tank (4) Each X-FEED Lind )2)Each X-FEED Lind )2)

The Filter drains are located on the outboard underside of the nacelles.The Filter drains are located on the outboard underside of the nacelles. The Tank drains are located beneath each wing.The Tank drains are located beneath each wing. Fuel Cross-Feed drains are located at the lowest point in the system, on Fuel Cross-Feed drains are located at the lowest point in the system, on

the underside of the fuselage just inboard of the trailing edge of the right the underside of the fuselage just inboard of the trailing edge of the right Flap.Flap.

Electrical SystemElectrical System The electrical system is capable of supplying current for complete The electrical system is capable of supplying current for complete

night IFR equipment.night IFR equipment. Supply is provided by two 65 amp alternators (one on each engine).Supply is provided by two 65 amp alternators (one on each engine). A 35 ampere-hour 12 volt battery provides current for starting and A 35 ampere-hour 12 volt battery provides current for starting and

for use of electrical equipment when the engines are not running.for use of electrical equipment when the engines are not running. The battery is located in the nose section and is accessible through The battery is located in the nose section and is accessible through

the nose compartment baggage door.the nose compartment baggage door. Piper offers an optional external power plug located on the lower left Piper offers an optional external power plug located on the lower left

side of the nose section. side of the nose section. An external power source or battery can be connected here without An external power source or battery can be connected here without

having to access the main battery.having to access the main battery.

Electrical SystemElectrical System

Approximately 2,000 RPM or more is required to obtain the full 65 Approximately 2,000 RPM or more is required to obtain the full 65 amps.amps.

It is NORMAL to have Zero output at idle RPM.It is NORMAL to have Zero output at idle RPM. This is due to the reduced drive ratio of the engine.This is due to the reduced drive ratio of the engine. Dual Ammeters and the ALT annunciator light provide monitoring of Dual Ammeters and the ALT annunciator light provide monitoring of

the electrical system.the electrical system. The Ammeters indicate the output from the alternators.The Ammeters indicate the output from the alternators. Should an alternator’s ammeter indicate a much higher load than Should an alternator’s ammeter indicate a much higher load than

normal, that alternator should be suspected of malfunction and normal, that alternator should be suspected of malfunction and switched OFF.switched OFF.

The remaining alternator should show a NORMAL load within 1 minute.The remaining alternator should show a NORMAL load within 1 minute.

Electrical SystemElectrical System If both ammeters indicate a higher than normal load for more than 5 If both ammeters indicate a higher than normal load for more than 5

minutes, and electrical defect should be considered because a discharged minutes, and electrical defect should be considered because a discharged battery will reduce the alternator load as it approaches the charged battery will reduce the alternator load as it approaches the charged condition.condition.

A Zero ammeter reading indicates the alternator is not producing current, A Zero ammeter reading indicates the alternator is not producing current, and should be accompanied by illumination of the ALT light.and should be accompanied by illumination of the ALT light.

A Single alternator is capable of supporting continued flight with exceptions:A Single alternator is capable of supporting continued flight with exceptions: -With Deicing equipment and other high loads, care must be exercised to -With Deicing equipment and other high loads, care must be exercised to

prevent loads exceeding 65 amps, and subsequently discharging the prevent loads exceeding 65 amps, and subsequently discharging the battery.battery.

When all electrical equipment is off (except master), the ammeters will When all electrical equipment is off (except master), the ammeters will indicate current being used to charge the battery, and operate instruments.indicate current being used to charge the battery, and operate instruments.

If the sum of the two meters is significant, this indicates a low battery If the sum of the two meters is significant, this indicates a low battery charge.charge.

The pilot should try to determine why the battery charge is low, and if no The pilot should try to determine why the battery charge is low, and if no cause is apparent, have the system checked.cause is apparent, have the system checked.

Electrical SystemElectrical System The Annunciator Panel on the upper left of the instrument panel The Annunciator Panel on the upper left of the instrument panel

includes lights for the following:includes lights for the following: Manifold Pressure OverboostManifold Pressure Overboost Gyro PressureGyro Pressure Oil PressureOil Pressure AlternatorAlternator Illumination of any light should draw the pilots attention and action Illumination of any light should draw the pilots attention and action

should be taken to verify the validity of the warning.should be taken to verify the validity of the warning. Light function may be tested with a push-to-test button.Light function may be tested with a push-to-test button. The auxiliary fuel pump lights will not illuminate with this test.The auxiliary fuel pump lights will not illuminate with this test. The auxiliary fuel pump lights will illuminate when the primer The auxiliary fuel pump lights will illuminate when the primer

switches are activated.switches are activated.

Electrical SystemElectrical System If both alternators should fail in flight, the battery becomes the If both alternators should fail in flight, the battery becomes the

primary source of electrical power.primary source of electrical power. All un-necessary equipment should be turned off.All un-necessary equipment should be turned off. Then time remaining on the battery is dependant on it’s charged Then time remaining on the battery is dependant on it’s charged

state at the time of alternator failure, and the time it took the pilot state at the time of alternator failure, and the time it took the pilot to recognize the problem and take corrective actions.to recognize the problem and take corrective actions.

During night or instrument flight the pilot should continually During night or instrument flight the pilot should continually monitor the ammeters and warning lights so prompt action can be monitor the ammeters and warning lights so prompt action can be taken if a malfunction occurs.taken if a malfunction occurs.

Electrical SystemElectrical System The electrical system is protected by circuit breakers located on The electrical system is protected by circuit breakers located on

the circuit breaker panel on the lower right side of the instrument the circuit breaker panel on the lower right side of the instrument panel.panel.

Breakers may be re-set after several minutes of cooling.Breakers may be re-set after several minutes of cooling.

Gyro Pressure SystemGyro Pressure System The Direction Gyro and Attitude Indicator are driven by positive air The Direction Gyro and Attitude Indicator are driven by positive air

pressure.pressure. A pressure pump on each engine takes air from the nacelle and passed A pressure pump on each engine takes air from the nacelle and passed

through pressure pumps.through pressure pumps. Pressure regulators mounted on the firewalls maintain the air at a Pressure regulators mounted on the firewalls maintain the air at a

constant pressure to prevent damage to the instruments.constant pressure to prevent damage to the instruments. Check-valvesCheck-valves

Pitot Static SystemPitot Static System Pitot Pressure is sensed by the Aluminum Pitot Head installed on Pitot Pressure is sensed by the Aluminum Pitot Head installed on

the bottom of the Left Wing and carried through lines to the the bottom of the Left Wing and carried through lines to the Airspeed Indicator on the instrument panelAirspeed Indicator on the instrument panel

Static Pressure for the Altimeter, Vertical Speed Indicator and Static Pressure for the Altimeter, Vertical Speed Indicator and Airspeed Indicator is sensed by 2 static ports located on each side Airspeed Indicator is sensed by 2 static ports located on each side of the rear fuselage near the Stabilatorof the rear fuselage near the Stabilator

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Pa 34 200t Seneca II