Citation Encore 560 Specifications

Operating Manual Member of GAMACOPYRIGHT ” 2000CESSNA AIRCRAFT COMPANYWICHITA, KANSAS, USA56OMB-01MODEL 560560-0539 THRU -500028 SEPTEMBER 2000REVI

INTRODUCTIONMODEL 560DEFINITIONS AND ABBREVIATIONSAC: Alternating CurrentAccelerate-Stop Distance: The distance required to accelerate the aircraft an

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-23. Tail Surface Deice SystemI2-50 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSENVIRONMENTALThe pressurization and air conditioning systems utilize engine bleed air to pressurize and air c

SECTION II AIRPLANE AND SYSTEMSMODEL 560During descent, the pilot can view the selected landing field altitude by pressing the FL button on thecontrol

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-24. Pressurization Control System SchematicI56OMB-01 Configuration AA 2-53

SECTION II AIRPLANE AND SYSTEMSMODEL 560AIR CONDITIONINGAir conditioning for the cabin is provided by routing engine bleed air through precoolers and

SECTION II MODEL 560 AIRPLANE AND SYSTEMSAn air cycle machine overheat sensor is installed between the compressor and turbine section of theair cycle

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-26. Bleed Air System SchematicI2-56 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSVAPOR CYCLE AIR CONDITIONINGA standard vapor cycle air conditioner using R134A refrigerant is available. It

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-27 Oxygen System SchematicI2-58 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-28. Pilot's Side Console Oxygen Control and OutletsWARNING•NO SMOKING WHEN OXYGEN IS BEING US

INTRODUCTIONMODEL 560Demonstrated Crosswind: The demonstrated crosswind velocity of 30 knots (measured at 30feet above the runway surface) is the velo

SECTION II AIRPLANE AND SYSTEMSMODEL 560CREW OXYGEN MASKSThe EROS crew mask is a quick donning diluter-demand/pressure breathing mask with integralmic

SECTION II MODEL 560 AIRPLANE AND SYSTEMSLIGHTINGINTERIOR LIGHTINGInterior lighting is provided for the flight compartment, cabin and tailcone area.

SECTION II AIRPLANE AND SYSTEMSMODEL 560EXTERIOR LIGHTINGExterior lighting consists of wing and tail mounted navigation lights, anti-collision lights

MODEL 560 SECTION II AIRPLANE AND SYSTEMS Figure 2-29. Annunciator Panel 1. BATT O’TEMP The red bat

SECTION II AIRPLANE AND SYSTEMSMODEL 5607. F/WSHUTOFFL RThe amber firewall shutoff light advises that the left and/or right fuel and hydraulic

SECTION II MODEL 560 AIRPLANE AND SYSTEMS21. EMERPRESSThe amber emergency pressurization light flashes and the master cautionilluminates to advise tha

SECTION II AIRPLANE AND SYSTEMSMODEL 56032. WINGANTI-ICEL ROn the ground, with left and/or right anti-ice switches selected to the WING/ENGINEp

SECTION II MODEL 560 AIRPLANE AND SYSTEMS37. AP ROLLMISTRIMThe amber autopilot roll mistrim light flashes and the master caution illuminatessteady to

SECTION II AIRPLANE AND SYSTEMSMODEL 560TEST SYSTEMThe test selector is located in the upper left corner of the pilot’s switch panel and offers severa

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSSECTION IIIINSTRUMENTATION AND AVIONICSCONTENTSPageInstrumentation . . . . . . . . . . . . . . . . .

INTRODUCTIONMODEL 560ISA: International Standard Atmosphere in which:a. The air is a dry perfect gas;b. The temperature at sea level is 15°C (59°F);c.

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSFigure 3-1 Instrument Panel (Typical)I56OMB-01 Configuration AA 3-3

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560INSTRUMENTATIONThe Citation Encore is equipped with a Primus 1000 Integrated Avionics System which inc

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSALTIMETER AND AIRSPEED INDICATIONSAltitude and airspeed data to the primary flight displays (PFD) are

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560Figure 3-2 Typical Airspeed DisplayI3-6 Configuration AA 56OMB-01

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSLOW AIRSPEED AWARENESSA red, amber, and white thermometer type display located on the inside of the a

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560An altitude trend vector is displayed on the left edge of the altitude tape and provides an indication

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSINCLINOMETERSConventional inclinometers (slip indicators) are fixed to the bezel of each primary flig

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560AMLCD INDICATING INSTRUMENTEach engine is equipped with the following instruments displayed on the cen

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSFigure 3-5 AMLCD Indicating InstrumentI56OMB-01 Configuration AA 3-11

INTRODUCTIONMODEL 560MHz: MegahertzMultiengine Normal Climb Maximum power setting recommended for normal multiengineThrust Setting climb.N1: Low press

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560The ITT gage is calibrated from 0 - 7500C. The temperature displayed is a synthetic inter-turbinetemp

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSSTANDBY FLIGHT DISPLAYA Meggitt Avionics Standby Flight Display (SFD) System indicator is located on

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560A built-in power up test system (PBIT) will automatically detect any failure of the display at power u

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSThe area at the lower part of the scale (0.57 to 0.1) represents the normal operating range of theair

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560DIGITAL CLOCK One model M877 digital clock is mounted on the left side of the pilot’s instrument pane

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSAVIONICSThe standard avionics package includes dual audio control panels, dual VHF COMM transceivers,

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560CONTROLS AND INDICATORSTuning of the COM radios is accomplished by three methods. The first method, d

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSA TX annunciation at the top of the COM frequency window will annunciate whenever the transmitteris a

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560The SQ push button toggles the COM squelch open and closed. When the squelch is open, SQ isannunciate

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSA comparator annunciator displays a flashing ACT to the left of the active frequency display when the

INTRODUCTIONMODEL 560Residual Ice: That ice which is not completely removed from the leading edge ofthe wing and horizontal stabilizer by the surface

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560The STO button is used to perform three separate functions. (1) When in the channel mode (NOT inprogr

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSHONEYWELL PRIMUS II REMOTE RADIO SYSTEM - AUDIO CONTROL UNITTwo Honeywell Primus II digital audio con

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560An ID/VOICE selector is located on the right center of the audio panel. It is not a latching switch,

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSNOTE• With passenger speaker mode selected and microphone selector switch selected tooxygen mask, the

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560VHF NAV (Optional)Dual VIR-432 navigation receivers provide VOR, localizer, glideslope and marker beac

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSANNUNCIATORSThe NAV control contains MEM (memory), RMT (remote), and HLD (hold) annunciators. The ME

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560Outer, middle, and inner marker receivers are incorporated in the VIR-432 receivers. The visualmarker

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSSTANDBY HORIZONTAL SITUATION INDICATOR (HSI)The standby horizontal situation indicator is a three-inc

SECTION IIIINSTRUMENTATION AND AVIONICSMODEL 560HONEYWELL PRIMUS II REMOTE RADIO SYSTEM - ADFThe automatic direction finder (ADF) function of the Prim

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSAUTOMATIC DIRECTION FINDER - COLLINS ADF-462 (Optional)The Collins ADF-462 is controlled by a CTL-6

INTRODUCTIONMODEL 560True Airspeed (KTAS): The airspeed (knots) of an airplane relative to undisturbed air.UHF: Ultra High FrequencyUnusable Fuel: Fue

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560The ADF bearing information may be selected on the "O" bearing needle of the pilot's e

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSThe marker beacon receivers are in operation whenever the NAV receivers are ON. They operate ona fre

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560EMERGENCY LOCATOR BEACONThe emergency locator beacon (ELT) system is an emergency transmitter designe

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSMODE ANNUNCIATIONFlight director mode annunciations are integral to the primary flight displays. The

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560MISCELLANEOUS ANNUNCIATIONS :AP FAIL Illuminates in amber to indicate automatic flight control system

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSThe selection of NAV 1, NAV 2 or FMS on the DC-550 display controller push-buttons controls thesource

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560When the bank limit mode is engaged, the autopilot maximum bank angle is limited to 14 degrees.When t

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSPRIMUS 1000 SYSTEM OPERATIONThe Primus 1000 system incorporates a wide variety of capabilities that p

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560VNAV MODEThe vertical navigation mode (VNAV) mode provides a means to define a climb or descent path

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSPROGRAMMINGProgramming is possible when a VOR station is tuned, lock-on of azimuth and DME occurs, an

INTRODUCTIONMODEL 560VR: The rotation speed is the speed at which rotation is initiated duringtakeoff to attain the V2 climb speed at or before a heig

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560Figure 3-21. Vertical Angle ComputationFigure 3-22. Intercepting Preset AngleI3-42 Configuration AA

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSTOUCH CONTROL STEERINGTouch control steering (TCS) enables the airplane to be maneuvered manually dur

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560For a VOR approach (VAPP mode), the desired VOR frequency is selected on the NAV receiver, thecourse

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSALTITUDE HOLD (ALT) AND ALTITUDE PRESELECT (ASEL)Selecting altitude hold (ALT) provides steering comm

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560GO-AROUND MODEA go-around mode (GA) is available through buttons on the left and right throttles. De

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSDISPLAY CONTROLLERThe display controllers, located on the left and right of the instrument panels, al

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560Decision Height Rotation of the "DH" knob adjusts the decision height display on the EADI.(

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSMULTIFUNCTION DISPLAY SYSTEM The Multifunction Display (MFD), the central DU-870 cathode ray tube, se

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560The MAP format is always oriented to the airplane heading and the airplane symbol is located at thec

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSMFD CONTROLSDim This knob controls overall MFD CRT dimming in addition to the automaticdimming featur

INTRODUCTIONMODEL 560STANDARD SYSTEM SYMBOLSStandard System Symbols have been developed and utilized in illustrated system diagrams throughoutthe Oper

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560MFD CONTROLSSKP The function of this button depends upon the type of MFD display:MAP or PLAN: Skips t

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSELECTRONIC ATTITUDE DIRECTOR INDICATOR (EADI)Certain displays form a permanent part of the electronic

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560Low Altitude Awareness - A “Low altitude awareness” indication of a solid brown raster band will appe

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSNOTEWhen the back course (BC) mode is selected on the flight director (the selectedcourse is more tha

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI)The displays in the EHSI portion of the PFD are discu

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSPART TIME DISPLAYSPart time displays are present when selected on the display controller or the fligh

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560ARC MODE (PARTIAL COMPASS FORMAT)During operation in the arc (WX) mode, additional presentations are

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSDISPLAY REVERSIONIn the event of failure of one of the display units, turning off the failed display

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560COMPARISON MONITORSelected pilot and copilot input data are compared in the symbol generator. If the

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSPULSE EQUIPMENTHONEYWELL PRIMUS II REMOTE RADIO SYSTEM - ATCThe ATC (transponder) function of the opt

INTRODUCTIONMODEL 560HYDRAULIC/PNEUMATIC SYSTEM SYMBOLS (Continued)PRESSURE SWITCHRESTRICTORGROUND SERVICE, EXTERNALQUICK DISCONNECTSSHUTOFF VALVE WIT

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560Only one transponder is in operation at one time; the opposite one is held in STANDBY forinstantaneou

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSDISTANCE MEASURING EQUIPMENTHONEYWELL PRIMUS REMOTE RADIO SYSTEM - DME The Primus II DME system ,the

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560NAV 1 or NAV 2 will be annunciated on the top line of the indicator to indicate which NAV is beingdis

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSThe IND-42C power switch (PWR) controls power to the indicator and to the DME-442receiver-transmitter

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560The radio altimeter system interfaces with the data acquisition units (DAUs) and the optional ground

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSThe Primus 660 ColoRadar System is an X-band alphanumeric digital radar with display designed forweat

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560CONTROLSTILT Rotary control used to select tilt angle of antenna beam with relation to earthplane. T

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSRCT Alternate action pushbutton enables the Rain Echo Attenuation CompensationTechnique (REACT) blue

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEMS (TCAS) (OPTIONAL)TCAS 1The optional TCAS 1 system is an

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSTCAS 1 has two sensitivity levels; SL A and SL B. SL A is invoked when the airplane is below 2000fee

INTRODUCTIONMODEL 560HYDRAULIC/PNEUMATIC SYSTEM SYMBOLS (Continued)SHUTTLE VALVECHECK VALVELANDING GEAR CONTROLMODULE MANIFOLD VALVE THREE-POSITION -

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560maneuvers. The following information is generated and considered by the TCAS II in making a decision

SECTION IIIMODEL 560 INSTRUMENTATION AND AVIONICSAREA NAVIGATIONGNS-XL FLIGHT MANAGEMENT SYSTEMThe GNS-XL Flight Management System is a comprehensive

SECTION III INSTRUMENTATION AND AVIONICSMODEL 560AIRBORNE FLIGHT INFORMATION SYSTEM (AFIS) (Optional)The Global Airborne Flight Information System (A

SECTION IVMODEL 560 OPERATING INFORMATIONOPERATING INFORMATIONTABLE OF CONTENTSPageNORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION IVMODEL 560 OPERATING INFORMATIONNORMAL PROCEDURESTABLE OF CONTENTSPageNORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION IVMODEL 560 OPERATING INFORMATIONNORMAL PROCEDURESPREFLIGHT INSPECTION1. Battery - CONNECTED.2. Engine Covers (2) - REMOVED.3. Pitot Covers (3

SECTION IV OPERATING INFORMATIONMODEL 560EXTERIOR INSPECTIONDuring inspection, make a general check for security, condition and cleanliness of the air

SECTION IVMODEL 560 OPERATING INFORMATIONNORMAL PROCEDURESPREFLIGHT INSPECTION1. Battery - CONNECTED.2. Engine Covers (2) - REMOVED.3. Pitot Covers (3

INTRODUCTIONMODEL 560FUEL SYSTEM SYMBOLSPUMP (EJECTOR)PUMP(FUEL PRESSURE (FP) DRIVEN)PUMP(DC MOTOR (DCM) DRIVEN)PUMP (ENGINE DRIVEN (ED))FLOAT SWITCHF

SECTION IV OPERATING INFORMATIONMODEL 560EXTERIOR INSPECTIONDuring inspection, make a general check for security, condition and cleanliness of the air

SECTION IVMODEL 560 OPERATING INFORMATIONEXTERIOR INSPECTION (Continued)e. Anti-Ice Bleed Air Cooling Air Inlet - CLEAR.f. Heated Leading Edge - CONDI

SECTION IV OPERATING INFORMATIONMODEL 560EXTERIOR INSPECTION (Continued)9. Left Nacelle - CHECK.a. Precooler Exhaust - CLEAR.b. Thrust Reverser Bucket

SECTION IVMODEL 560 OPERATING INFORMATIONCOCKPIT PREPARATION (Continued)f. IGNITION Switch - NORM.g. Fuel CROSSFEED Switch - OFF.h. Anti-Ice/Deice -

SECTION IV OPERATING INFORMATIONMODEL 560COCKPIT PREPARATION (Continued)13. Warning Systems - TEST/OFF.NOTEThe W/S TEMP annunciator may not test after

SECTION IVMODEL 560 OPERATING INFORMATIONCOCKPIT PREPARATION (Continued)f. IGNITION Switch - NORM.g. Fuel CROSSFEED Switch - OFF.h. Anti-Ice/Deice -

SECTION IV OPERATING INFORMATIONMODEL 560COCKPIT PREPARATION (Continued)13. Warning Systems - TEST/OFF.NOTEThe W/S TEMP annunciator may not test after

SECTION IVMODEL 560 OPERATING INFORMATIONSTARTING ENGINES (Continued)g. Fuel, Oil, Generator and Hydraulic Annunciators - EXTINGUISHED (respective eng

SECTION IV OPERATING INFORMATIONMODEL 560BEFORE TAXI (Continued)2. Flight Controls/Speed Brakes/Flaps - CHECKED/SET.NOTEVerify flaps trim interconnect

SECTION IVMODEL 560 OPERATING INFORMATIONBEFORE TAXI (Continued)b. Radio Altimeter - SET.c. Altimeters - SET and CROSS CHECK.d. Heading - CROSS CHECK.

INTRODUCTIONMODEL 560FUEL SYSTEM SYMBOLS (Continued)CHECK VALVERELIEF VALVESHUTOFF VALVE - NORMAL OPEN (MANUALLY OPERATED)SHUTOFF VALVE - NORMAL CLOSE

SECTION IV OPERATING INFORMATIONMODEL 560BEFORE TAKEOFF1. Flaps - SET.2. Speed Brakes - RETRACTED.3. Trims - (3) SET FOR TAKEOFF.4. Anti-ice/Deice - A

SECTION IVMODEL 560 OPERATING INFORMATIONBEFORE TAXI (Continued)b. Radio Altimeter - SET.c. Altimeters - SET and CROSS CHECK.d. Heading - CROSS CHECK.

SECTION IV OPERATING INFORMATIONMODEL 560BEFORE TAKEOFF1. Flaps - SET.2. Speed Brakes - RETRACTED.3. Trims - (3) SET FOR TAKEOFF.4. Anti-ice/Deice - A

SECTION IVMODEL 560 OPERATING INFORMATIONAFTER TAKEOFF - CLIMB1. Landing Gear - UP.2. Flaps - UP.3. Throttles - SET CLIMB N1.4. ENGINE SYNC Knob - ON

SECTION IV OPERATING INFORMATIONMODEL 560DESCENT1. DEFOG Fan - HI or LOW (minimum of 15 minutes prior to descent). 2. Pilot and Copilot Foot Warmers

SECTION IVMODEL 560 OPERATING INFORMATIONAPPROACH (Continued)12. Landing at airports above 11,500 feet:a. PRESS SOURCE Select Knob - OFF (below 15,000

SECTION IV OPERATING INFORMATIONMODEL 560LANDING 1. Throttles - IDLE.NOTEEight seconds after touchdown, engines will spool down from flight idle to gr

SECTION IVMODEL 560 OPERATING INFORMATIONAFTER LANDING1. Thrust Reversers - STOW.CAUTIONDO NOT ADVANCE THROTTLES UNTIL THE THRUST REVERSER UNLOCKLIGHT

SECTION IV OPERATING INFORMATIONMODEL 560DRY MOTORING1. Throttle - OFF.2. IGNITION Switch - OFF.3. FUEL BOOST Pump - ON.4. ENGINE START Button - PRESS

SECTION IVMODEL 560 OPERATING INFORMATIONSPECIAL PROCEDURESSHORT FIELD OPERATIONFor takeoff, taxi into position as close to the approach end as possib

INTRODUCTIONMODEL 560BLEED AIR/DEICE AND VACUUM SYSTEM SYMBOLSCONTROLHEAT EXCHANGERTEMPERATURE CONTROL UNITPRESSURE REGULATING AND SHUTOFF VALVE TWO-P

SECTION IV OPERATING INFORMATIONMODEL 560ADVERSE FIELD CONDITIONS All flight manual field length data assumes a dry, hard surface runway except where

SECTION IVMODEL 560 OPERATING INFORMATIONBIRD INGESTION PRECAUTIONS Studies have indicated that bird strikes are most likely from the surface to appro

SECTION IV OPERATING INFORMATIONMODEL 560The abbreviated checklist is designed to enable the crew to perform all prestart functions in advance.This pe

SECTION IVMODEL 560 OPERATING INFORMATIONWHEEL FUSIBLE PLUG CONSIDERATIONSBrake application reduces the speed of an airplane by means of friction betw

SECTION IV OPERATING INFORMATIONMODEL 560FLIGHT INTO ICING Flight into known icing is the intentional flight into icing conditions that are known to e

SECTION IVMODEL 560 OPERATING INFORMATIONPROCEDURE FOR ADDING DIETHYLENE GLYCOL MONOMETHYL ETHER (DIEGME) FUELADDITIVE NOTEService experience has show

SECTION IV OPERATING INFORMATIONMODEL 560COLD WEATHER OPERATIONSCOLD SOAKOperation of the airplane has been demonstrated after prolonged exposure to g

SECTION IVMODEL 560 OPERATING INFORMATIONCOLD WEATHER OPERATIONS 2. Engine Start Preparation:a. Engine preheat should not be required for engine oil t

SECTION IV OPERATING INFORMATIONMODEL 560GROUND DEICE/ANTI-ICE OPERATIONSDuring cold weather operations, flight crews are responsible for ensuring the

SECTION IVMODEL 560 OPERATING INFORMATIONNOTE• Tables do not apply to other than SAE or ISO Type I, Type II, or Type IV FPD fluids.•The responsibility

INTRODUCTIONMODEL 560OXYGEN SYSTEM SYMBOLSOXYGEN CYLINDERGAGEFILLER VALVE AND PROTECTIVE CAPOVERBOARD DISCHARGE INDICATOR (VENT PORT)MASK (CREW)I56OMB

SECTION IV OPERATING INFORMATIONMODEL 5605610X1001ENGINE INLETS CLEAREDFROM ALL SNOW, ICE ANDSLUSH BY HAND ONLYLANDING GEAR DOORSAND WHEEL WELLS MUSTB

SECTION IVMODEL 560 OPERATING INFORMATION 5610X1001NOTE: SHADED AREAS INDICATEESSENTIAL AREAS TO BEANTI-ICED.MINIMUM DIRECTSPRAY AREAS: ENGINE INLETS

SECTION IV OPERATING INFORMATIONMODEL 560SERVICINGFUELA variety of fuels can be used in the airplane, but each must have anti-icing additive incorpora

SECTION IVMODEL 560 OPERATING INFORMATIONOILEach engine oil tank has an oil filler neck with a cap assembly. Oil is added to each engine directlythro

SECTION IV OPERATING INFORMATIONMODEL 560ALCOHOLAn alcohol reservoir is located next to the brake reservoir behind the right baggage compartment aftli

SECTION IVMODEL 560 OPERATING INFORMATIONAIRPLANE CLEANING AND CAREPAINTED SURFACESThe exterior of a new airplane is painted with a polyurethane two-c

SECTION IV OPERATING INFORMATIONMODEL 560The application of both AGE MASTER Number 1 and ICEX should be in accordance with themanufacturer's reco

SECTION VMODEL 560 ABNORMAL PROCEDURESABNORMAL PROCEDURESTABLE OF CONTENTSPAGEABNORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VABNORMAL PROCEDURESMODEL 560FLIGHT CONTROLSElectric Elevator Runaway Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VMODEL 560 ABNORMAL PROCEDURESABNORMAL PROCEDURESTABLE OF CONTENTSPAGEABNORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . .

INTRODUCTIONMODEL 560ELECTRICAL SYMBOLSCAPACITORCIRCUIT BREAKERCURRENT TRANSFORMERDIODEThe switch contacts connect toan annunciator system to warnwhen

SECTION VABNORMAL PROCEDURESMODEL 560FLIGHT CONTROLSElectric Elevator Runaway Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VMODEL 560 ABNORMAL PROCEDURESABNORMAL LANDINGSingle-Engine Approach and Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VMODEL 560 ABNORMAL PROCEDURESABNORMAL PROCEDURESENGINE FAILURE/PRECAUTIONARY SHUTDOWN1. AP TRIM DISC Button - PRESS and RELEASE.2. Rudder and

SECTION VABNORMAL PROCEDURESMODEL 560AIRSTART ENVELOPEFigure 3-3I5-6 Configuration AA 56OMB-01

SECTION VMODEL 560 ABNORMAL PROCEDURESABNORMAL PROCEDURESENGINE FAILURE/PRECAUTIONARY SHUTDOWN1. AP TRIM DISC Button - PRESS and RELEASE.2. Rudder and

SECTION VABNORMAL PROCEDURESMODEL 560AIRSTART ENVELOPEFigure 3-3I5-6 Configuration AA 56OMB-01

SECTION VMODEL 560 ABNORMAL PROCEDURESENGINE START MALFUNCTION (ENGINE DOES NOT START ON GROUND)1. Throttle - OFF.2. ENGINE START DISENGAGE Button - P

SECTION VABNORMAL PROCEDURESMODEL 560LOW FUEL PRESSURE (LO FUEL PRESS L OR R CAUTION LIGHT ON)1. FUEL BOOST Pump Switch- ON.2. L or R BOOST and L or R

SECTION VMODEL 560 ABNORMAL PROCEDURESENGINE START MALFUNCTION (ENGINE DOES NOT START ON GROUND)1. Throttle - OFF.2. ENGINE START DISENGAGE Button - P

INTRODUCTIONMODEL 560ELECTRICAL SYMBOLS (Continued)FUSE/LIMITERGROUNDLAMPMETER/INDICATORMICROPHONEMOTORI56OMB-01 Configuration AA Introduction-21

SECTION VABNORMAL PROCEDURESMODEL 560LOW FUEL PRESSURE (LO FUEL PRESS L OR R CAUTION LIGHT ON)1. FUEL BOOST Pump Switch- ON.2. L or R BOOST and L or R

SECTION VMODEL 560 ABNORMAL PROCEDURESENGINE DISPLAY FAILURE (BLANK DISPLAY CHANNEL)1. Engine Display Reversion Switch - L or R. (Switch to operating

SECTION VMODEL 560 ABNORMAL PROCEDURESFIREWALL SHUTOFF VALVE CLOSED (F/W SHUTOFF L OR R CAUTION LIGHT ON)Indicates the fuel and hydraulic firewall shu

SECTION VABNORMAL PROCEDURESMODEL 560ENGINE VIBRATION (ENG VIB L OR R ADVISORY LIGHT ON) (Continued)IF VIBRATION EXISTSON GROUND2. Correct prior to fl

SECTION VMODEL 560 ABNORMAL PROCEDURESFIREWALL SHUTOFF VALVE CLOSED (F/W SHUTOFF L OR R CAUTION LIGHT ON)Indicates the fuel and hydraulic firewall shu

SECTION VABNORMAL PROCEDURESMODEL 560ENGINE VIBRATION (ENG VIB L OR R ADVISORY LIGHT ON) (Continued)IF VIBRATION EXISTSON GROUND2. Correct prior to fl

SECTION VMODEL 560 ABNORMAL PROCEDURESAFT J-BOX CURRENT LIMITER OR CIRCUIT BREAKER (AFT J BOX LMT OR CB CAUTION LIGHTON)Indicates either an open curre

SECTION VABNORMAL PROCEDURESMODEL 560ENVIRONMENTAL SYSTEM AIR DUCT OVERHEAT (AIR DUCT O'HEAT CAUTION LIGHT ON)1. TEMP Circuit Breaker (LH Panel)

SECTION VMODEL 560 ABNORMAL PROCEDURESEMERGENCY PRESSURIZATION ON (AUTOMATIC ACTUATION) (EMER PRESS CAUTION LIGHTON) AND CABIN ALTITUDE (CAB ALT WARNI

INTRODUCTIONMODEL 560ELECTRICAL SYMBOLS (Continued)REGULAR - resistance does not change.TEMPERATURE CONTROLLED - resistance changes with the temperatu

SECTION VABNORMAL PROCEDURESMODEL 560CABIN PRESSURIZATION CONTROLLER FAILURE (AMBER LED ILLUMINATED)NOTEDetection of auxiliary control will be indicat

SECTION VMODEL 560 ABNORMAL PROCEDURESELECTRIC TRIM INOPERATIVE1. PITCH TRIM Circuit Breaker (LH panel) - CHECK IN.IF STILL INOPERATIVE2. Manual Eleva

SECTION VABNORMAL PROCEDURESMODEL 560AUTOPILOT OUT OF TRIM (AP ROLL MISTRIM OR AP PITCH MISTRIM CAUTION LIGHT ON)(Continued)NOTEBe prepared for minor

SECTION VMODEL 560 ABNORMAL PROCEDURESWING ANTI-ICE FAILURE (WING ANTI-ICE L OR R CAUTION LIGHT ON AND MASTER CAUTION)1. Throttle (affected side) - IN

SECTION VABNORMAL PROCEDURES MODEL 560WING ANTI-ICE FAILURE (WING ANTI-ICE L OR R CAUTION LIGHT ON AND MASTER CAUTION)(Continued)BEFORE LANDING (wit

SECTION VMODEL 560 ABNORMAL PROCEDURESWING BLEED AIR OVERHEAT (WING O'HEAT L OR R CAUTION LIGHT ON)IF ANTI-ICE SWITCH IS WING/ENG ONCONTINUOUS IL

SECTION VABNORMAL PROCEDURES MODEL 560TAIL DEICE FAILURE (TL DEICE FAIL L OR R CAUTION LIGHT ON) (Continued)3. Passenger Advisory Lights - PASS SAFET

SECTION VMODEL 560 ABNORMAL PROCEDURESTAIL DEICE TIMER FAILURE (TL DEICE PRESS L OR R ADVISORY LIGHT FAILS TO ILLUMINATEOR CONTINUES TO CYCLE OR TL DE

SECTION VABNORMAL PROCEDURES MODEL 560WINDSHIELD AIR OVERHEAT (WS AIR O'HEAT CAUTION LIGHT ON) (Continued)WS AIR O'HEAT CONTINUOUS ILLUMINA

SECTION VMODEL 560 ABNORMAL PROCEDURESWINDSHIELD BLEED AIR FAILURELOSS OF HOT AIR SUPPLY (VALVE WILL NOT OPEN OR POSSIBLE LINE FAILURE) 1. W/S BLEED

MODEL 560 INTRODUCTIONELECTRICAL SYMBOLS (Continued)ROTARY OR MULTI POSITIONDOUBLE POLE/DOUBLE THROW (DPDT) mayhave OFF position in the center. Dashed

SECTION VABNORMAL PROCEDURES MODEL 560ANGLE-OF-ATTACK PROBE HEATER FAILURE (AOA HTR FAIL CAUTION LIGHT ON)Indicates that the angle of attack probe he

SECTION VMODEL 560 ABNORMAL PROCEDURESIC - PFD WRAP AROUND TEST FAIL (CHECK PFD I, CHECK PFD 2 CAUTION LIGHT ON)Indicates IC to PFD communication wrap

SECTION VABNORMAL PROCEDURES MODEL 560LOSS OF TAS INPUT TO FLIGHT GUIDANCE SYSTEM1. Failure Side - DETERMINE.NOTE• Failure of TAS input to the pilot’

SECTION VMODEL 560 ABNORMAL PROCEDURESDISPLAY GUIDANCE COMPUTER COOLING FAN FAILURE (IC-1 OR IC-2 FAN MESSAGE ON MFD)ON GROUNDIndicates failure of the

SECTION VABNORMAL PROCEDURES MODEL 560NOSE AVIONIC FAN FAILURE (NOSE AVN FAN CAUTION LIGHT ON)ON GROUND1. Ground Operating Time - LIMIT TO 30 MINUTES

SECTION VMODEL 560 ABNORMAL PROCEDURESLANDING GEAR WILL NOT EXTEND (Continued)IF GEAR EXTENDS INTO THE LOCKED POSITION5. EMERGENCY GEAR RELEASE - PULL

SECTION VABNORMAL PROCEDURES MODEL 560WHEEL BRAKE FAILURE1. Brake Pedals - REMOVE FEET from BRAKE PEDALS.2. EMER BRAKE Handle - PULL as required.CAUT

SECTION VMODEL 560 ABNORMAL PROCEDURESLANDING GEAR WILL NOT EXTEND (Continued)IF GEAR EXTENDS INTO THE LOCKED POSITION5. EMERGENCY GEAR RELEASE - PULL

SECTION VABNORMAL PROCEDURES MODEL 560WHEEL BRAKE FAILURE1. Brake Pedals - REMOVE FEET from BRAKE PEDALS.2. EMER BRAKE Handle - PULL as required.CAUT

SECTION VMODEL 560 ABNORMAL PROCEDURESANTISKID SYSTEM FAILURE (ANTISKID INOP CAUTION LIGHT ON AND LO BRK PRESS CAUTIONLIGHT EXTINGUISHED) (Continued)I

SECTION VABNORMAL PROCEDURES MODEL 560SINGLE-ENGINE APPROACH AND LANDING (Continued)12. Pressurization - CHECK ZERO DIFFERENTIAL PRIOR TO LANDING.13.

SECTION VMODEL 560 ABNORMAL PROCEDURESFLAPS INOPERATIVE APPROACH AND LANDING (NOT IN LANDING POSITION)1. Flap Override Switch - GPWS FLAP OVRD ON (amb

SECTION VABNORMAL PROCEDURES MODEL 560CABIN DOOR PRESSURE SEAL FAILURE (DOOR SEAL CAUTION LIGHT ON)ON GROUND1. Correct prior to flight.IN FLIGHT1. Al

SECTION VMODEL 560 ABNORMAL PROCEDURESUSE OF SUPPLEMENTAL OXYGEN (UNPRESSURIZED)1. Oxygen Masks - NORMAL below 25,000 feet cabin altitude.- 100% at or

SECTION VABNORMAL PROCEDURES MODEL 560INADVERTENT ICING ENCOUNTER1. WING/ENGINE Anti-Ice L and R Switches - ON.2. W/S BLEED Switch - LOW or HI.3. TAI

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY PROCEDURESTABLE OF CONTENTSPAGEEMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY PROCEDURESTABLE OF CONTENTSPAGEEMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY PROCEDURESENGINE FAILURE OR FIRE, OR MASTER WARNING DURING TAKEOFFSPEED BELOW V1 - TAKEOFF SHOULD BE

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSSECTION 1DESCRIPTION AND SPECIFICATIONSPageGeneral Description . . . . . . . . . . . . . . . . . . .

SECTION VIEMERGENCY PROCEDURES MODEL 560ENGINE FIRE (LH OR RH ENGINE FIRE WARNING LIGHT ON)4. IGNITION Switch (affected engine) - NORM.5. Throttle (a

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY RESTART - TWO ENGINES4. If altitude allows - INCREASE AIRSPEED to 200 KIAS.5. ENGINE FIRE Switches -

SECTION VIEMERGENCY PROCEDURES MODEL 560Figure 3-1AIRSTART ENVELOPEI6-6 Configuration AA 56OMB-01

SECTION VIMODEL 560 EMERGENCY PROCEDURESMAXIMUM GLIDE - EMERGENCY LANDING (Continued)7. Passenger Advisory Lights - PASS SAFETY.8. Passenger Briefing

SECTION VIEMERGENCY PROCEDURES MODEL 560THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued)SPEED ABOVE V1 - TAKEOFF SHOULD NORMALLY BE

SECTION VIMODEL 560 EMERGENCY PROCEDURESMAXIMUM GLIDE - EMERGENCY LANDING (Continued)7. Passenger Advisory Lights - PASS SAFETY.8. Passenger Briefing

SECTION VIEMERGENCY PROCEDURES MODEL 560THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued)SPEED ABOVE V1 - TAKEOFF SHOULD NORMALLY BE

SECTION VIMODEL 560 EMERGENCY PROCEDURESTHRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued)18. Speed Brakes - RETRACT (50 feet AGL and b

SECTION VIEMERGENCY PROCEDURES MODEL 560THRUST REVERSER INADVERTENT INFLIGHT DEPLOYMENT (Continued)NOTEIf possible, the runway used for landing shoul

SECTION VIMODEL 560 EMERGENCY PROCEDURESTHRUST REVERSER UNLOCK LIGHT ON IN FLIGHTIF LIGHT WILL NOT EXTINGUISH3. L/R THRUST REVERSER Circuit Breakers (

LOG OF EFFECTIVE PAGESMODEL 560LOG OF EFFECTIVE PAGESUse this page to determine the currency and applicability of your Operating Manual. Pages affect

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560DESCRIPTION AND SPECIFICATIONSPageOperating Limitations (Continued)Oxygen Mask . . . . . . . . . . . .

SECTION VIEMERGENCY PROCEDURES MODEL 560OVERPRESSURIZATION (Continued)8. PRESS SOURCE Select Knob - OFF.9. Descend to 15,000 feet MSL or Minimum Safe

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY DESCENT5. Airspeed - MMO/VMO (use reduced speed if structural damage has occurred).6. Transponder -

SECTION VIEMERGENCY PROCEDURES MODEL 560SMOKE REMOVALNOTENo action is normally required; however, if smoke is intense:NOTEHeadsets or hats worn by th

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKE (Continued)KNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. L

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING.10. La

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKE (Continued)KNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. L

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING.10. La

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKE (Continued)KNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. L

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF.10. Land as soon as practical (within

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKE (Continued)KNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. L

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSGENERAL DESCRIPTIONThe Cessna Citation Encore is certified in accordance with FAR Part 25 airworthine

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF.10. Land as soon as practical (within

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKEKNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. Land as soon

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF.10. Land as soon as practical (within

SECTION VIMODEL 560 EMERGENCY PROCEDURESELECTRICAL FIRE OR SMOKE (Continued)KNOWN SOURCE5. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate.6. L

SECTION VIEMERGENCY PROCEDURES MODEL 560ELECTRICAL FIRE OR SMOKE (Continued)9. WINDSHIELD BLEED AIR Knobs - OFF.10. Land as soon as practical (within

SECTION VIMODEL 560 EMERGENCY PROCEDURESBATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON)NOTEIf current decreases and battery voltage is 1 volt l

SECTION VIEMERGENCY PROCEDURES MODEL 560LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTERWARNING)1. L/R GEN Switches - RESET THEN

SECTION VIMODEL 560 EMERGENCY PROCEDURESBATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON)NOTEIf current decreases and battery voltage is 1 volt l

SECTION VIEMERGENCY PROCEDURES MODEL 560LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTERWARNING)1. L/R GEN Switches - RESET THEN

SECTION VIMODEL 560 EMERGENCY PROCEDURESBATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON)NOTEIf current decreases and battery voltage is 1 volt l

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560ENVIRONMENTAL CONTROLCabin pressurization utilizes bleed air from the engines which is routed through

SECTION VIEMERGENCY PROCEDURES MODEL 560LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTERWARNING)1. L/R GEN Switches - RESET THEN

SECTION VIMODEL 560 EMERGENCY PROCEDURESLOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTERWARNING) (Continued)NOTEWhen flaps are at

SECTION VIEMERGENCY PROCEDURES MODEL 560AC POWER FAILURE (AC FAIL AND MASTER WARNING LIGHTS ON) AND DUAL INVERTERFAILURE (MASTER CAUTION AND INVTR FA

SECTION VIMODEL 560 EMERGENCY PROCEDURESLOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTERWARNING) (Continued)WHEN LANDING ASSURED6

SECTION VIEMERGENCY PROCEDURES MODEL 560AC POWER FAILURE (AC FAIL AND MASTER WARNING LIGHTS ON) AND DUAL INVERTERFAILURE (MASTER CAUTION AND INVTR FA

SECTION VIMODEL 560 EMERGENCY PROCEDURESPFD/MFD RED GUN FAILUREThe failure of a red gun in an electronic display indicator results in the following pr

SECTION VIEMERGENCY PROCEDURES MODEL 560AUTOPILOT GLIDESLOPE DEVIATION PROFILECONDITIONS:Airspeed - VREFFlaps - LandGear - DownDelay - One second fro

SECTION VIMODEL 560 EMERGENCY PROCEDURESEMERGENCY EVACUATION7. Airplane and Immediate Area - CHECK for BEST ESCAPE ROUTE.IF THRU CABIN DOOR8. Cabin Do

SECTION VIEMERGENCY PROCEDURES MODEL 560DITCHING (Continued)WATER CONTACT1. Aircraft Pitch Attitude - Slightly higher than Normal Landing Attitude.2.

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCESECTION VIIFLIGHT PLANNING AND PERFORMANCECONTENTSPageWEIGHT AND BALANCE . . . . . . . . . . . . .

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSFigure 1-1. Three View DrawingI56OMB-01 Configuration AA 1-5

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEWEIGHT AND BALANCEThe center-of-gravity (CG) of an airplane can be defined as the point on the lon

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560AIRPLANE WEIGHING INFORMATIONAt maximum gross weight, the center-of-gravity of a loaded airplane ca

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCESAMPLE LOADING PROBLEMStandard AirplaneBasic Empty Weight - 10,176 pounds.* 100 pounds of baggage

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 56010. Subtract the fuel and moment used for taxi. A standard 200-pound burnoff is assumed. Themomen

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-3. Weight and Balance FormI56OMB-01 Configuration AA 7-7

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-4. Fuel Loading Weight and Moment Table

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-5. Center-of-Gravity Limits EnvelopeCENTER-OF-GRAVITY LIMITS ENVELOPEI56OMB-01 Configura

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560MULTIENGINE NORMAL CLIMBANTI-ICE SYSTEMS - OFFFigure 7-6. Multiengine Normal ClimbI7-10 Configurat

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEMULTIENGINE NORMAL CLIMBANTI-ICE SYSTEMS - ONFigure 7-7. Multiengine Normal ClimbI56OMB-01 Config

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560SPECIFICATIONSDIMENSIONSLength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560MAXIMUM CRUISE THRUST SETTINGANTI-ICE SYSTEMS - OFFFigure 7-8. Maximum Cruise Thrust SettingI7-12

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEMAXIMUM CRUISE THRUST SETTINGANTI-ICE SYSTEMS - ONFigure 7-9. Maximum Cruise Thrust SettingI56OMB

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560FLIGHT PLANNINGThorough flight planning suggests establishing a preflight goal such as maximum rang

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEThe following criteria are used:1. 200 pounds of taxi fuel.2. 247 Knot /.62 Mach climb schedule fo

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 1 of 14)I7-16 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 2) I56OMB-01 Configuration AA 7-17

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 3)I7-18 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 4)I56OMB-01 Configuration AA 7-19

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 5)I7-20 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 6) I56OMB-01 Configuration AA 7-21

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSOPERATING LIMITATIONSWEIGHTMaximum Design Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . .

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 7)I7-22 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 8)I56OMB-01 Configuration AA 7-23

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 9)I7-24 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 10)I56OMB-01 Configuration AA 7-25

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 11)I7-26 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 12) I56OMB-01 Configuration AA 7>27

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-10. Maximum Cruise Thrust (Sheet 13) I7-28 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-10. Maximum Cruise Thrust (Sheet 14) I56OMB-01 Configuration AA 7>29

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-11. Normal Cruise Thrust (Sheet 1 of 10) I7-30 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-11. Normal Cruise Thrust (Sheet 2) I56OMB-01 Configuration AA 7>31

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560EXAMPLE: Pressure Altitude - 25,000 FEETWeight - 16,630 POUNDSMaximum Maneuvering Speed - 236 KNOTSFig

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-11. Normal Cruise Thrust (Sheet 3) I7-32 Configuration AA 56OMB-01

SECTION VIIMODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-11. Normal Cruise Thrust (Sheet 4) I56OMB-01 Configuration AA 7>33

SECTION VIIFLIGHT PLANNING AND PERFORMANCEMODEL 560Figure 7-11. Normal Cruise Thrust (Sheet 5) I7-34 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-11 Normal Cruise Thrust (Sheet 6) I56OMB-01 Configuration AA 7-35

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-11 Normal Cruise Thrust (Sheet 7) I7-36 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-11 Normal Cruise Thrust (Sheet 8) I56OMB-01 Configuration AA 7-37

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-11 Normal Cruise Thrust (Sheet 9) I7-38 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-11 Normal Cruise Thrust (Sheet 10) I56OMB-01 Configuration AA 7-39

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 1 of 16) I7-40 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 2) I56OMB-001 Configuration AA 7-41

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSNOTE: Ambient Air Temperature Limit is indicated Ram Air Temperature (RAT) adjusted forRam rise (refe

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 3) I7-42 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 4) I56OMB-001 Configuration AA 7-43

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 5) I7-44 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 6) I56OMB-001 Configuration AA 7-45

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 7) I7-46 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 8) I56OMB-001 Configuration AA 7-47

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 9) I7-48 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 10) I560OMB-01 Configuration AA 7-49

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 11) I7-50 Configuration AA 560OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 12 ) I560OMB-01 Configuration AA 7-51

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560APPROACH AND LANDING IN ICING CONDITIONSWhen any residual ice is present or can be expected during app

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 13) I7-52 Configuration AA 560OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 14) I560OMB-01 Configuration AA 7-53

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-12 Long Range Cruise (Sheet 15) I7-54 Configuration AA 560OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-12 Long Range Cruise (Sheet 16) I56OMB-01 7-55/7-56(Blank)

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCECLIMBMultiengine climb performance is presented in tabulated form on the following pages. The cl

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560 I7-58 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCE I56OMB-01 Configuration AA 7-59

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560 I7-60 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCECRUISESpecific performance data are presented on the following pages for various combinations of

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSFigure 1-5. Engine Overspeed LimitsAREAA- NO ACTION REQUIRED.AREAB- RECORD IN ENGINE LOGBOOK.AREAC-

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560 I7-62 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 2) I56OMB-01 Configuration AA 7-63

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 3) I7-64 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 4) I56OMB-01 Configuration AA 7-65

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 5) I7-66 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 6) I56OMB-01 Configuration AA 7-67

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 7) I7-68 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 8) I56OMB-01 Configuration AA 7-69

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 9) I7-70 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 10) I56OMB-01 Configuration AA 7-71

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560Figure 1-6. Interturbine Temperature LimitsI1-12 Configuration AA 56OMB-01

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 11) I7-72 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 12) I56OMB-01 Configuration AA 7-73

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 13) I7-74 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 14) I56OMB-01 Configuration AA 7-75

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 15) I7-76 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 16) I56OMB-01 Configuration AA 7-77

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 17) I7-78 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 18) I56MB-01 Configuration AA 7-79

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 19) I7-80 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 20) I56MB-01 Configuration AA 7-81

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSBATTERY AND STARTER CYCLE LIMITATIONSNOTES1. If battery limitation is exceeded, a deep cycle includin

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 21) I7-82 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 22) I56MB-01 Configuration AA 7-83

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 23) I7-84 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 24) I56MB-01 Configuration AA 7-85

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 25) I7-86 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 26) I56OMB-01 Configuration AA 7-87

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 27) I7-88 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 28) I56OMB-01 Configuration AA 7-89

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 29) I7-90 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 30) I56OMB-01 Configuration AA 7-91

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560HYDRAULIC FLUIDApproved Fluids: Use Skydrol 500A, B, B-4, C or LD-4; or Hyjet, Hyjet W, III, IV, IVA,

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 31) I7-92 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 32) I56OMB-01 Configuration AA 7-93

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 33) I7-94 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-14 Cruise (Sheet 34) I56OMB-01 Configuration AA 7-95

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-14 Cruise (Sheet 35) I7-96 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-15 Cruise (Sheet 1 of 10) I56OMB-01 Configuration AA 7-97

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-15 Cruise (Sheet 2) I7-98 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-15 Cruise (Sheet 3) I56OMB-01 Configuration AA 7-99

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-15 Cruise (Sheet 4) I7-100 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-15 Cruise (Sheet 5) I56OMB-01 Configuration AA 7-101

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONS NOTES1. Maximum Asymmetrical Fuel Differential for normal operations is 200 pounds. 2. Flight charac

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-15 Cruise (Sheet 6) I7-102 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-15 Cruise (Sheet 7) I56OMB-01 Configuration AA 7-103

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-15 Cruise (Sheet 8) I7-104 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-15 Cruise (Sheet 9) I56OMB-01 Configuration AA 7-105

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-15 Cruise (Sheet 10) I7-106 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEDESCENTPerformance for two types of descent is presented on the following pages. Time, distance

SECTION VIIFLIGHT PLANNING AND PERFORMANCE MODEL 560Figure 7-16 Normal Descent I7-108 Configuration AA 56OMB-01

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-17 High Speed Descent I56OMB-01 Configuration AA 7-109/7-110(Blank)

SECTION VII MODEL 560 FLIGHT PLANNING AND PERFORMANCEFigure 7-18 Holding FuelHOLDINGHolding fuel in total pounds per hour is presented for various we

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560FUEL LIMITATIONSAnti-icing must be added to all approved fuels not presently containing additive.FUEL

INDEXMODEL 560INDEXAAbbreviations . . . . . . . . . . . . . . . Introduction-6Abnormal Procedures . . . . . . . . . . . . . . . . . 5-1Aborted Takeof

INDEXMODEL 560INDEXCenter-of-Gravity Limitations . . . . . . . . . . . . 1-7Center-of-Gravity LimitsEnvelope . . . . . . . . . . . . . . . . . . . . .

INDEXMODEL 560INDEXFFilters, Fuel . . . . . . . . . . . . . . . . . . . . . . . 2-17Fire Bottles . . . . . . . . . . . . . . . . . . . . . . . 4-38Fir

INDEXMODEL 560INDEXLighting, Exterior . . . . . . . . . . . . . . . . . . . 2-62Lighting, Interior . . . . . . . . . . . . . . . . . . . . 2-61Lightin

INDEXMODEL 560INDEXPerformance, Airplane . . . . . . . . . . . . . . 7-1/7-2Climb . . . . . . . . . . . . . . . . . . . . . . . 7-57Cruise . . . . . .

INDEXMODEL 560INDEXTire Pressure . . . . . . . . . . . . . . . . . . . . . . 1-16Touch Control Steering . . . . . . . . . . . . . . . 3-43To/From Bias

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSLOAD FACTORIn Flight:Flaps - UP Position (0°) . . . . . . . . . . . . . . . . . . . . . . . . . .$1.4

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560MANEUVERSNo acrobatic maneuvers, including spins, are approved. No intentional stalls are permitted a

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSINSTRUMENT MARKINGSLeft and Right Oil Pressure Indicators . . . . . . . . . . . . . . . . . . Red Li

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEMThe Honeywell Primus 1000 Display and Flight Guidance Syst

SECTION IMODEL 560 DESCRIPTION AND SPECIFICATIONSSTANDBY FLIGHT INSTRUMENTS1. A satisfactory preflight test must be accomplished on the standby gyro s

MODEL 560 INTRODUCTIONCONTENTSSECTIONINTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRODUCTION-1DESCRIPTION AND S

SECTION IDESCRIPTION AND SPECIFICATIONSMODEL 560ANGLE-OF-ATTACK / STICK SHAKER SYSTEMThe angle-of-attack and stall warning system must be operable and

SECTION II MODEL 560 AIRPLANE AND SYSTEMSSECTION IIAIRPLANE AND SYSTEMSCONTENTSPageENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SECTION II MODEL 560 AIRPLANE AND SYSTEMSENGINEGENERALJet engines produce thrust by accelerating air. It is the product of the mass of the air times

SECTION II MODEL 560 AIRPLANE AND SYSTEMS Figure 2-1 Engine Airflow and Cross Section NOTES • When practicing touch and go landi

SECTION II MODEL 560 AIRPLANE AND SYSTEMSENGINE SYNCHRONIZER (Continued)Alternating current from the fan and turbine monopoles is routed into the con

SECTION II AIRPLANE AND SYSTEMSMODEL 560DEFINITIONS:AGB - ACCESSORY GEAR BOXMOP - MAIN OIL PRESSURE (DIFFERENTIAL)MOT - MAIN OIL TEMPERATUREBRG - BEAR

SECTION II MODEL 560 AIRPLANE AND SYSTEMSTHRUST REVERSER SYSTEMDESCRIPTION AND OPERATION The thrust reversers are of the external target type employin

SECTION II MODEL 560 AIRPLANE AND SYSTEMS Control of the individual thrust reverser i

MODEL 560 SECTION II AIRPLANE AND SYSTEMS During thrust reverser deploym

SECTION II AIRPLANE AND SYSTEMSMODEL 560After deployment, power may be increased by moving the thrust reverser throttle levers aft formaximum reverse

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-6. Thrust Reverser Hydraulic System Schematic (Sheet 1 of 3)I56OMB-01 Configuration AA 2-11

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-6. Thrust Reverser Hydraulic System Schematic (Sheet 2 of 3 )I2-12 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-6. Thrust Reverser Hydraulic System Schematic (Sheet 3 of 3)I56OMB-01 Configuration AA 2-13

SECTION II AIRPLANE AND SYSTEMSMODEL 560FIRE PROTECTION Engine fire detection consists of a closed-loop sensing system and detector control unit which

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFUELGENERALThe Citation Encore fuel system is made up of two distinct, but essentially identical halves. Nor

SECTION II AIRPLANE AND SYSTEMSMODEL 560EJECTOR PUMPSFour ejector pumps in each fuel cell utilize existing fuel pressure in conjunction with a venturi

SECTION II MODEL 560 AIRPLANE AND SYSTEMSENGINE FUEL SYSTEM The two-stage, engine-driven pump mounted on the accessory gearbox supplies high pressure

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-10 (Sheet 1 of 2) Fuel System SchematicI2-18 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-10 (Sheet 2 of 2) Fuel System SchematicI56OMB-01 Configuration AA 2-19

INTRODUCTIONMODEL 560INTRODUCTIONUNIT AND SERIAL NUMBEROn all Model 560 Citation Encore airplanes, the serial and unit number are stamped into the air

SECTION II AIRPLANE AND SYSTEMSMODEL 560HYDRAULICGENERALThe Main hydraulic system is an open-center type system. Two engine-driven pumps (one on eache

SECTION II MODEL 560 AIRPLANE AND SYSTEMSPUMPSHydraulic pressure is provided by two positive displacement engine-driven pumps, each mounted on theengi

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-12. Hydraulic System SchematicI2-22 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSLANDING GEAR AND BRAKESGENERALThe landing gear is electrically controlled and hydraulically actuated. Each m

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-13 (Sheet 1 of 2) Landing Gear Extension and Retraction Flow DiagramI2-24 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-13 (Sheet 2 of 2) Landing Gear Extension and Retraction Flow DiagramI56OMB-01 Configuration AA 2-25

SECTION II AIRPLANE AND SYSTEMSMODEL 560POSITION AND WARNING SYSTEMThe landing gear position and warning system provides visual and audible indication

SECTION II MODEL 560 AIRPLANE AND SYSTEMSWHEEL BRAKESToe-actuated multiple disc brakes are installed on the main gear wheels. Braking can beaccomplis

SECTION II AIRPLANE AND SYSTEMSMODEL 560A switch on the instrument panel allows the pilot to select antiskid ON or OFF. When the switch is inthe ON p

SECTION II MODEL 560 AIRPLANE AND SYSTEMSPNEUMATICGENERALAn air bottle which provides for emergency extension of the landing gear and/or emergency bra

INTRODUCTIONMODEL 560AIRPLANE CONFIGURATION CODES (Continued)Configuration Effectivity byCodeSerial NumberAH Airplanes 560-0626 thru -0644 not incorpo

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-16 (Sheet 1 of 2) Wheel Brake Hydraulic SystemSchematic I2-30 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-16 (Sheet 2 of 2) Wheel Brake Hydraulic SystemI56OMB-01 Configuration AA 2-31

SECTION II AIRPLANE AND SYSTEMSMODEL 560FLIGHT CONTROLSGENERALAll aerodynamic controls, with the exception of the flaps and speed brakes, are mechanic

SECTION II MODEL 560 AIRPLANE AND SYSTEMSRUDDERRudder control is effective at all flight speeds. Full rudder deflection is 22°, ±1° either side ofce

SECTION II AIRPLANE AND SYSTEMSMODEL 560When the speed brakes are fully retracted, the control valve closes, the hydraulic system bypass valveopens an

SECTION II MODEL 560 AIRPLANE AND SYSTEMSELECTRICALGENERALElectrical power is normally supplied by two 28.5-volt direct current (DC), 300-ampere, engi

SECTION II AIRPLANE AND SYSTEMSMODEL 560DIRECT CURRENT (DC) POWERThe direct current (DC) power generation system consists of two starter/generators,

SECTION II MODEL 560 AIRPLANE AND SYSTEMSCIRCUIT BREAKERSPush-to-reset, pull-off type circuit breakers, with the amperage rating marked on each breake

SECTION II AIRPLANE AND SYSTEMSMODEL 560EMERGENCY BATTERYPlacing the battery switch in the EMER position opens the battery relay. The emergency bus r

SECTION II MODEL 560 AIRPLANE AND SYSTEMSENGINE STARTINGDepressing either engine start button closes the respective start relay and provides DC power

INTRODUCTIONMODEL 560COVERAGEThis manual is intended to provide an information source for familiarization, review and suggestedtechnique to achieve ma

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-18. Alternating Current Electrical System Schematic (Sheet 1 of 2)I2-40 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-18. Alternating Current Electrical System Schematic (Sheet 2 of 2)5674T1001I56OMB-01 Configuration

SECTION II MODEL 560 AIRPLANE AND SYSTEMS 2-42 Configuration AA

MODEL 560 SECTION II AIRPLANE AND SYSTEMS 56OMB-01 Configuration AA 2-43

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-20. Direct Current Electrical System SchematicI2-44 Configuration AA 56OMB-01

SECTION II MODEL 560 AIRPLANE AND SYSTEMSANTI-ICE/DEICE SYSTEMS The anti-ice systems consist of bleed air heated engine inlets, wing leading edges, fa

SECTION II AIRPLANE AND SYSTEMSMODEL 560NOTEfIcing conditions exist when the indicated RAT on the ground and for takeoff is +10°C(+50°F) or below; the

SECTION II MODEL 560 AIRPLANE AND SYSTEMSTAIL DEICEThe horizontal tail is deiced by pneumatic boots controlled by the tail deice AUTO/OFF MANUALswitch

SECTION II AIRPLANE AND SYSTEMSMODEL 560Figure 2-23. Pilot’s Switch Panel with Anti-ice System ControlsAn additional temperature sensor is located

SECTION II MODEL 560 AIRPLANE AND SYSTEMSFigure 2-22. Wing Bleed Air Anti-ice SystemI56OMB-01 Configuration AA 2-49