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Revision 1

Citation VII

Operating Handbook

Use of Operating Handbook

The CAE Operating Handbook is both a training aid for the simulator and a practical tool for the cockpit. This handbook is comprised of three sections.• The normal procedures section (N-pages) are inserted in vinyl sleeves for

increaseddurabilityandeaseofpage replacement.ThechecklistsprovidedareCAE-developedStandardOperating Procedures (SOP). If your company has itsownSOP,youmayreplacetheCAESOPwithyourownSOP.

• Theflightplanningsection(F-pages)containschartsandgraphstofacilitateflightplanning.

• The emergency/abnormal procedures section (E-pages) contains checklists foremergency and abnormal situations. All immediate action (memory) items areprintedinred;procedureswithimmediateactionitemsalsohaveredtitles.

Thissectionmaybeaccessedinoneofthreeways:bytableofcontents(EMERtab,front),bysystemtab(front),orbynumberedtab(back).

If youareaccessingaprocedureby the tableofcontentsorbysystem,simplyplaceyourthumbonthepropertabandopenthebook.Forexample,placeyourthumbontheEMERtabandopenthehandbook;theE-pagestableofcontentsisdisplayed.

Ifyouareaccessingtheproceduresbycockpitindication,referencethebackpageof this handbook. Locate the appropriate item and note the number in the adjacent circle.Next,locatethesimilarlynumberedtab;placeyourthumbonthatpageandopen the handbook. The procedure will be on one of the two pages now open or immediatelyfollowing.

DEFINITIONS

LandAs SoonAs Possible: Land at the nearest suitable airport. Extreme situationscouldrequireanoff-airportlanding.Primaryconsiderationissafetyofoccupants.LandAs SoonAs Practical: Land at a suitable airport. Primary consideration is theurgencyof theemergencyorabnormalsituation.Continuingto thedestinationoranalternatewithappropriateservicefacilitiesmaybeanoption.WARNING: ANOPERATINgPROCEDuRE,TEChNIquE,ETC.,ThATMAyRESuLT

IN PERSONAL INjuRy OR LOSS OF LIFE IF NOT CAREFuLLyFOLLOwED.

CAUTION: Anoperatingprocedure,technique,etc.,thatmayresultindamagetoequipmentifnotcarefullyfollowed.

NOTE: An operating procedure, technique, etc., considered essential toemphasize.

NOTICE:ThisOperatinghandbookistobeusedforaircraftfamiliarizationandtrainingpurposesonly.Itisnottobeusedas,norconsideredasubstitutefor,themanufacturer’sPilotorMaintenanceManuals.

Copyright©2012,CAE,Inc.Allrightsreserved.

Excerptedmaterialsusedinthispublicationhavebeenreproducedwiththepermissionof

CessnaAircraftCompany.

PrintedintheunitedStatesofAmerica.

SEVERE ICING ENCOUNTERDURING ALL ICING ENCOUNTERS MAINTAIN A MINIMUM OF 180 KIAS

EXCEPT FOR APPROACH AND LANDINGIcing Conditions exist anytime the indicated RAT is +10°C and below when visible moisture in any form is present. Aircraft Ice Protection Systems should be operating when in icing conditions.

IF SEVERE ICING IS PRESENT:1. ATC – IMMEDIATELY REQUEST PRIORITY HANDLING TO

FACILITATE EXITING THE SEVERE ICING CONDITIONS2. Flaps – LEAVE IN CURRENT POSITION3. Autopilot – DISENGAGE�Caution:� BE PREPARED FOR CONTROL WHEEL FORCE

REQUIRED TO MAINTAIN DESIRED FLIGHT PATH.4. Maneuvering – AVOID ABRUPT AND EXCESSIVE MANEUVERING

THAT MAY AGGRAVATE CONTROL PROBLEMS.5. Angle-of-Attack – REDUCE IF UNUSUAL OR UNCOMMANDED

ROLL IS ENCOUNTERED (INCREASE AIRSPEED).Severe icing may be encountered at temperatures as cold as -18°C. Increased vigilance is required at 0°C ambient temperature with visible moisture present. The following visual cues indicate severe icing conditions: � Visible rain at temperatures colder than 0°C ambient air

temperature. � Droplets that splash or splatter at temperatures colder

than 0°C ambient air temperature. � Unusually extensive ice accumulation on the airframe

and windshield in areas not normally observed to collect ice.

� Accumulation of ice on the upper surface of the wing aft of protected area.

Aircraft equipment has not been designed to provide protection against freezing rain or severe conditions of mixed or clear ice. During all operations, the pilot is expected to exercise good judgment and be prepared to alter the flight plan, i.e. exit icing, if conditions exceed the capability of the aircraft and equipment.Freezing rain and clear ice will be deposited in layers over the entire surface of the airplane and can “run back” over control surfaces before freezing. Ice accumulations significantly alter the shape of airfoils and increase the weight of the aircraft. Flight with ice accumulated on the aircraft will increase stall speeds and alter the speeds for optimum performance.

06/12

Normal Procedures

Citation VII Operating HandbookFor Training Purposes Only July 12 N-1

continued on next page

SEVERE ICING ENCOUNTER - CONTINUEDFlight at high angle-of attack (low airspeed) can result in ice building on the underside of the wings and the horizontal tail aft of areas protected by boots or leading edge anti-ice systems.Prolonged flight with the flaps and/or landing gear down is not recommended at 0°C ambient temperature with visible moisture present.Trace or light amounts of icing on the horizontal tail can significantly alter airfoil characteristics which will affect stability and control of the aircraft.

Normal Procedures

Citation VII Operating HandbookFor Training Purposes Only July 12N-2

continued from previous page

PF Pilot Flying. The pilot responsible for controlling the aircraft. Performs tasks and responds to checklist challenges.

PM Pilot Monitoring. Reads checklist challenges.(BOTH) PF and PM both perform the task and respond to the

challenge.* Indicates first flight of the day items.

COCKPIT INSPECTION PM PF OXYGEN MASKS & PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . .CHECK PASSENGER OXYGEN . . . . . . . . . AUTO (OFF, if above 12,000 ft MSL) CIRCUIT BREAKERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK PARK BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET AUXILIARY HYDRAULIC POWER SWITCH . . . . . . . . . . . . . . . . . . . OFF THROTTLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CUTOFF BATTERY SWITCH . . . . . . . . . . . . . . . . . . . EMER, CHECK EMER BUS BATTERY SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BATT 24V MIN BATTERY DISC SWITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK LANDING GEAR HANDLE . . . . . DOWN, INDICATES DOWN/LOCKED ENGINE FIRE SWITCHES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK GROUND EXTERNAL POWER . . . . . . . . . . . . . . CONNECT (if desired)* FLAP HANDLE . . . . . . . . . . . . . . .SET 20° (handle and indicator agree) FUEL QUANTITY AND BALANCE . . . . . . . . . . . . . . . . . . . . . . . CHECK FREON AIR CONDITIONING (if installed) . . . . . . . . . . . . . AS DESIREDoiutn:� External power must be used to operate the fern air

conditioning system when airplane's generator is not on line.

HOT ITEMS/LIGHTS . . . . . . . CHECK (Engine/Pitot Covers Removed)oiutn:� � Expedite the following checks if external power or APU

power is not being used.

� Items which can be observed from the cockpit may be turned off. All other items must be checked by a quick walk-around or a second crew member outside.

a. Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONb. Check illumination interior and exterior . . . . . . . . . . . . . . . . OFFc. Exterior Lights . . . . . . . . . . . . . .ON, CHECK ILLUMINATION OFFd. RAT, Pitot Static Switches . . . . . . ON, 30 SECONDS, THEN OFFe. VERIFY RAT, STATIC PORTS, PITOT TUBES, AOA PROBES,

WARMf. Left & Right Engine Anti-Ice Switches ON, 30 seconds, then

OFFg. VERIFY LH/RH WING FAIRING, LH/RH GENERATOR and

ALTERNATOR INLETS, WARM BATTERY SWITCH AS REQ: . . . . . . . . . . . . . OFF or BATT

(if external power or APU is on)

Normal Procedures


PM PFCABIN INSPECTION

* Portable Oxygen Bottle . . . . . . . . . . . . . . . . .SERVICED AND SECURE* Portable Fire Extinguisher . . . . . . . . . . . . . . .SERVICED AND SECURE* Door Entry Lights . . . . . . . . . . . . . . . . . . . . . . . .CHECK/AS REQUIRED* Cabin Door Water Barrier (if required) . . . . . ABOARD AND STOWED* Luminescent Exit Placard . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SECURE* Passenger Seats . . . . . . . . . . . . . . . . . . . . .UPRIGHT AND OUTBOARD* Emergency Exit . . . . . . . . . . . . SECURE; Handle Lock Pin — REMOVE* Gear Retract Hydraulic Shutoff Valve . . . . . CHECK HANDLE DOWN* Manual FUS TANK XFER T-Handle . . . . . . . . . . . . . . CHECK STOWED

COCKPIT PREPARATION Cockpit and Exterior Inspections . . . . . . . . . . . . . . . . . . . . COMPLETE Standby Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . .ON, UNCAGED,

VERIFY NO OFF FLAG, TEST, CAGEoiutn:� � The Standby Attitude Indicator is left on to initiate the

AHRS ground alignment procedure.

� The airplane should not be moved prior to completing the AHRS ground alignment (approximately three minutes). Any movement will cause the alignment process to restart.

Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BATT (24 volts min.) APU START (if desired) Park Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM SET Ground Recognition/NAV Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

a. APU Master Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONb. APU Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PRESS, CHECKc. RH Boost Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONd. APU Start Switch . . . . . . . . . . . . . . . . . . . PRESS MOMENTARILYe. APU RPM and EGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

After READY TO LOAD LIGHT ILLUMINATESf. APU Generator Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONg. APU Bleed Air Switch . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

Environmental Control Panel . . . . . ALL KNOBS SET TO 12 O'CLOCK WEMAC BOOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Ground Idle Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Ignition Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Generator Switches . . . . . . . . . AS REQ. (OFF for APU or GPU starts) Antiskid Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Fuel Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM/AS REQ’D

Normal Procedures


continued on next page

PM PF Fuel Computers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Avionics Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AC XOVER Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK WARNING SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK RUDDER BIAS HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST PAC BLEED SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST/SET Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Stabilizer . . . . . . . . . . . . . . . . . . . . VERIFY INDICATOR AGREES WITH

ACTUAL POSITION Secondary/Primary Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK EFIS Test Buttons . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH Aileron/Spoiler T-Handle. . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED IN CVR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

IF APU WITH HYDRAULICS Aileron Boost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK, SET Speed Brake Spoiler System . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Auxiliary Hydraulic Power Switch . . . . . . . . . . . . . . . . . . . . . . . . .NORM Audio Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET ATIS & Clearance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN Flight Instruments & FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Fuel Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Fuel Totalizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET VMO Schedule Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET

Alternate schedule may be selected if zero fuel weight is 15,350 Ibs or less. Normal must be used if zero fuel weight is more than 15,350 Ibs.

Takeoff Data and Bugs . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND SET

Normal Procedures


continued from previous page

PM PFBEFORE STARTING ENGINES

Cabin Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CLOSE and LOCK (check 11 green alignment indicators)

Passenger Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE Seats, Seat Belts, Shoulder Harnesses and Rudder Pedals . . . . . .SET Standby Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . ON, CAGED Emergency Light Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BATT Generator Switches . . . . . . . . . . .GEN (OFF for GPU start/first engine

start from APU then X GEN for second engine start) Passenger Advisory Light . . . . . . . . . . . . . . . . . . . . . . . . . . PASS SAFE Ground Recognition/NAV Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Door Unlocked Annunciators. . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Air Conditioner (if Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Avionics Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

ENGINE START APU Bleed Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CLOSED Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START Ground Idle Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Engine Gauges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Hydraulic Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Ground External Power (if used) . . . . . . . . . . . . . . . . . . . DISCONNECT Air Conditioner (if Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF DC Volts/Amps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Fuel Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM

BEFORE TAXI Avionics Power and AC XOVER . . . . . . . . . . . . . . . . . . . ON AND NORM Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET CADC Aileron Boost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK, SET Speed Brake Spoiler System . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Auxiliary Hydraulic Power Switch . . . . . . . . . . . . . . . . . . . . . . . . .NORM Fuel Control Manual Governors/Rudder Bias . . . . . . . . . . . . . .CHECK APR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST Emergency Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Flight Instruments & FMS . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY SET Ice Protection Systems . . . . . . . . . . . . . . . . . . . .CHECK, then. AS REQ. Nose Wheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Control Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Heading Phase Check . . . . . . . . . . . . . . . . . 6° MAXIMUM DIFFERENCE

Normal Procedures


PM PFTAXI

Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELEASE Brakes and Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK* Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK (*If intended to use on landing and first flight after maintenance)

BEFORE TAKEOFF Seats, Seat Belts, Shoulder Harnesses . . . . . . . . . . .CHECK SECURE Standby Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . .UNCAGED Flight Instruments and Flight Director . . . . . . . CHECK AND SET FOR

TAKEOFF Altitude Select . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND SET FOR TAKEOFF Speed Brakes/Spoiler Lever . . . . . . . . . . . . . . . . . . . . .FULL FORWARD Trims . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND SET FOR TAKEOFF Confirm Assigned Runway for Takeoff and Check Heading Indicator Agreement . . . . . . . . . ASSIGNED RUNWAY CONFIRMED, HEADING CHECKED Crew Brief . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE

CLEARED FOR TAKEOFF Control Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FREE Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK, TA/RA Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON RAT/Pitot Static Heat Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Windshield Heat Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Annunciator Panel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK APR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM F.A.T.S. (Flaps/Annunciators/Trims/Steering/Speeds/Speed Brakes)

TAKEOFF(STERILE COCKPIT BELOW 10,000 FT AGL)

Thrust . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR AND TRIM AT 60 KIAS

Normal Procedures


PM PFAFTER TAKEOFF (MINIMUM 1,500 FT AGL)

Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP (after positive climb)

LANDING Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTED HYD Pressure and Volume . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Flaps (at V2 + 25 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR CLIMB APR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISARM Engine Synchronizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Engine Bleed Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY ON Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Baggage Heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ.

10,000 FT MSL Passenger Advisory Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

FL 180 Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET 29.92 Recognition Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . SHUT DOWN (prior to 30,000 ft) Air Conditioning (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

CRUISE Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Fuselage Fuel Tank Transfer Switch . . .OFF (when transfer complete) Crew Oxygen Mask (when required) . . . . . . . . . . . DON AND NORMAL

Normal Procedures


MULTI-ENGINE EN-ROUTE CLIMB – N1%CITATION VII

TFE-731-4PA 1000

FT RAM AIR TEMPERATURE – °C

45 35 25 15 5 0 -5 -10 -15- -25 -35 -45 -55

SL 93.3 –

95.4 –

97.2 –

95.8 –

94.1 94.3

93.2 93.4

92.4 92.6

91.5 91.7

90.7 90.9

89.0 89.8

– 87.5

– 85.7

– 84.0

5 93.3 –

95.4 –

97.2–

98.7 –

98.9 98.4

98.0 98.3

97.1 97.3

96.2 96.4

95.2 95.4

93.4 93.5

91.6 91.5

89.8 89.6

88.0 87.6

10 93.3 –

95.4 –

97.2 –

98.7 –

99.9 98.4

100.4 99.2

100.8 99.9

101.2 100.6

100.1 100.5

98.1 98.5

96.1 96.5

94.1 94.5

92.0 92.5

15 93.3 –

95.4 –

97.2 –

98.7 –

99.9 98.0

100.4 98.8

100.8 99.6

101.2 100.4

101.5 101.3

101.5 101.5

101.2 101.5

99.2 101.5

97.0 100.2

20 91.3 –

93.1 –

95.0 –

96.9 –

98.8 97.3

99.7 98.2

100.6 99.0

101.2 99.9

101.5 100.8

101.5 101.5

101.5 101.5

101.5 101.5

101.5 100.2

25 90.5 –

92.4 –

94.3 –

96.2 –

98.1 96.4

99.0 97.3

100.0 98.2

101.2 99.1

101.5 99.1

101.5 101.5

101.5 101.5

101.5 101.5

101.5 101.5

30 90.2 –

92.1 –

93.9 –

95.8 –

97.7 95.2

98.7 96.2

99.6 97.1

100.5 98.1

101.5 99.1

101.5 101.1

101.5 101.5

101.5 101.5

101.5 100.2

35 98.4 –

91.2 –

93.1 –

95.0 –

96.8 –

97.7 92.5

98.7 93.9

99.6 95.3

100.6 96.7

101.5 99.6

101.5 101.5

101.5 101.5

101.5 100.2

41 88.1 –

90 –

91.9 –

93.7 –

95.6 –

96.6 –

97.5 –

98.5 –

99.4 –

101.5 97.3

101.5 99.6

101.5 101.5

101.5 100.2

43 87.9 89.7 91.6 93.5 95.4 96.3 97.3 98.2 99.2 101.1 101.5 101.5 101.5 45-51 87.6 89.4 91.3 93.2 95.1 96 97 97.6 98.9 100.8 101.5 101.5 101.5

� Values shown are for anti-ice OFF

oiutn:� � Set N1 Value or ITT = 924°C, whichever is achieved first� Upper Value = Anti-Ice OFF� Lower Value = Anti-Ice ON

Normal Procedures


MAXIMUM CRUISE THRUST SETTING – N1%CITATION VII

TFE-731-4PA 1000

FT RAM AIR TEMPERATURE – °C

10 5 0 -5 -10 -15 -20 -25 -30 -35 -40 -50 -60

10 95.896.2

94.795.1

93.693.9

92.592.8

91.491.7

90.390.6

89.289.5

88.188.4

87.087.2

85.886.1

--85.0

----

----

15 97.096.9

97.797.6

98.598.3

98.999.1

97.698.0

96.396.7

95.095.5

93.794.2

92.493.0

91.191.7

89.890.5

87.287.9

84.685.4

20 97.096.1

97.797.0

98.597.8

99.398.6

100.099.5

100.7100.3

101.5101.2

101.5101.5

-->-->

25 97.095.3

97.796.2

98.597.1

99.398.0

100.098.9

100.799.8

101.5100.8

101.5101.5

-->-->

31 96.993.7

97.694.7

98.495.8

99.296.8

100.097.9

100.799.0

101.5100.0

101.5101.1

101.5101.5

-->-->

33 96.692.2

97.593.4

98.394.6

99.195.8

100.097.1

100.798.3

101.599.5

101.5100.7

101.5101.5

-->-->

35 96.390.8

97.392.2

98.193.6

99.094.9

99.996.3

100.797.6

101.599.0

101.5100.4

101.5101.5

-->-->

37 96.089.4

97.190.9

97.992.4

98.993.9

99.895.4

100.797.0

101.598.5

101.5100.0

101.5101.5

-->-->

39 95.888.0

97.089.5

97.891.1

98.792.6

99.894.1

100.795.7

101.597.2

101.598.8

101.5100.3

101.5101.5

-->-->

41 95.586.6

96.888.2

97.689.7

98.691.3

99.792.8

100.794.4

101.596.0

101.597.5

101.599.1

101.5100.7

101.5101.5

-->-->

43° 94.3 95.6 96.7 97.8 99.0 100.2 101.3 101.5 -->45° 93.0 94.3 95.7 97.0 98.3 99.6 101.0 101.5 -->47° 91.9 93.3 94.7 96.1 97.5 98.9 100.3 101.2 101.5 -->

� Values shown are for anti-ice OFF

oiutn:� � Set N1 Value or ITT = 910°C, whichever is achieved first � Upper Value = Anti-Ice OFF� Lower Value = Anti-Ice ON

Normal Procedures


PM PFTURBULENT AIR PENETRATION

Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Airspeed . . . . . . . . . . . . . . . .200 KIAS or 0.75 MACH whichever is less Attitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONSTANT If Autopilot is On . . . . . . . . . . . . . . . . . . ALTITUDE HOLD, DISENGAGE

� Do not chase altitude or airspeed � Avoid sudden large control movements

DESCENT Windshield Defog Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Pilot and Copilot Side Window Vents . . . . . . . . . . . . . . . . . . . .CLOSED Windshield Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . .HT ON (if desired) Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND SET Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ.

FL 180 Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Recognition Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Air Conditioning (if installed) . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

10,000 FT (STERILE COCKPIT) Passenger Advisory Light . . . . . . . . . . PASS SAFE APU AS DESIRED Landing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPUTE AND SET Seats, Seat Belts, Shoulder Harnesses . . . . . . . . . . .CHECK SECURE Passenger Brief . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPLETED

APPROACH Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Radio Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . OFF (wing and fuselage) Engine Synchronizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Crew Brief . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..COMPLETE Flaps . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED (approach schedule)

Normal Procedures


PM PFBEFORE LANDING

Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON HYD Pressure/Volume . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Nose Wheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING SCHEDULE Annunciator Panel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Autopilot/Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

ALL-ENGINES GO-AROUND Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET GO AROUND POWER Airplane Pitch Attitude . . . . . . . . . . . . . POSITIVE ROTATION TO + 10° Speed brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT Flaps . . . . . . . . . . . . . . . . . . . . . SET TO APPROACH FLAP SCHEDULE Climb Speed . . . . . . . . . . . . . . . . . . . . VAPP (per landing flap schedule) Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . UP (after positive climb) Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTED Flaps (at V2 + 25 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. UP Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR CLIMB

LANDING Speed brakes and Spoilers . . . . . . . . . . . . . . . . . . . . . . . . . . . .DEPLOY Brakes . . . . . . . . . . . . . . . . . . APPLY after nose wheel ground contact Thrust Reversers (After Nose Wheel Is Firmly On Ground) . .DEPLOY

AFTER LANDING Nose Wheel Steering ON Light . . . . . . . . . . . . . . . . . . . . . . VERIFY ON Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STOW Spoilers/Speedbrakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT All Anti - Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQ. Rat/Pitot Static Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORM Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQ. RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STANDBY Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . STANDBY/OR AS REQ Baggage Heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Control Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (rotary test)

Normal Procedures


PM PFSHUTDOWN

Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTED Park Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Auxiliary Hydraulic Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Defog fan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF All Anti - Ice Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Air Conditioning (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Flight Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RECORD Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Standby Attitude Indicator . . . . . . . . . . . . . . . . . . . . . . . . . CAGED/OFF Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Throttles . . . . . . .CUTOFF (after two minutes below 38% fan RPM (N1) If APU running continue with APU shut down. Passenger Advisory Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Battery switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

APU SHUTDOWN APU Gen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF APU Bleed Air Switch . . . . . . . . . . . . . . . . . . . . AS PER INSTALLATION RPM Zero . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APU MASTER Passenger Advisory Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Normal Procedures


PM PFLOCAL TRAINING

AFTER LANDING – TAXI BACK Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFIED ON Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOWED Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF Spoilers/Speedbrakes . . . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF Pitot Heat/Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF W/S Bleed Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED Baggage Heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Primary Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

BEFORE TAKEOFF Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 SET Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRMED SET Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED Fuel Quantity/Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED TOLD Cards/Bugs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE

LINE UP APR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON RAT/PAT/STAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED Strobe/Exterior Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Annunciator Panel. . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED/NORMAL F.A.T.S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Flight Director . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

TRAFFIC PATTERN CLIMB Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMAL APR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISARM Anti-Ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED

Normal Procedures


PM PFAPPROACH AND LANDING

TOLD Cards/Bugs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Crew Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPROACH Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Ignition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN AND LOCKED Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTENDED Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED Annunciator Panel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKED Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LAND Autopilot and Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Normal Procedures


Normal Procedures


�Tis page ntentionallly left lannk�

Flight Planning

Citation VII Operating HandbookFor Training Purposes Only July 2012 F–1

simplified takeoffcriteria

The majority of takeoff situations result in field length margins that permit using a single set of values for speeds and power settings for takeoff. If the following conditions are met, the simplified procedures may be used.

1. No obstacle in flight path (cabin and cockpit bleed air on)2. Throttles — SET to applicable chart value, trim at 60 KIAS3. Anti-ice systems OFF4. 20° flaps5. Takeoff field length available = 6,000 ft or longer6. No tailwind7. No runway gradient

The values to be used are as follows:

FlApS 20°

WeiGHt 22,000 lbs or less

20,000 lbs or less

18,000 lbs or less

Airport Altitude 2,000 ft or below

4,000 ft or below

6,000 ft or below

Ambient Temperature between

11 and 30°C 10 and 31°C 6 and 35°C

V1 Vr V2 S/E Climb

takeoff fan Climb Fan S/E

122 kias 123 kias 133 kias 165 KIAS

98.0% RpM 94.6% RpM


97.8% RpM 94.4% RpM


97.1% RpM 93.4% RpM

When conditions are other than those specified in the simplified criteria; the appropriate tabulated data must be referred to.

Flight Planning

Citation VII Operating HandbookFor Training Purposes Only July 2012F–2

takeoff field lenGtH takeoffDetermine takeoff field length, V1, Vr, V2, and Venr and correct for runway gradient, anti-icing and ApR requirements.If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available.

TAKEOFF CORRECTIONS – FlApS 7°

If the runway has a gradient and/or the airplane anti-ice system is on, the following correction factors must be applied to the distances and V1 speeds.

rUnWaY Gradient

WeiGHt ranGe – poUnds

23,000-18,000V1*

17,999-15,000V1*

2% Uphill Use Vr Use Vr

1.5% Uphill Use Vr Use Vr

1% Uphill add 5 kts add 5 kts

1% Downhill add 1 kt add 1 kt

2% Downhill sUBtract 1 kt sUBtract 1 kt

Anti-ice ON add 4 kts add 4 kts

* If adjusted V1 is greater than VR use Vr for V1.

�Note:� For contaminated runway takeoff data, see AFM Section VII

Citation VII with TFE731-4 Engines

Flight Planning


takeoff field lenGtH takeoff

Determine takeoff field length, V1, Vr, V2, and Venr and correct for runway gradient, anti-icing and ApR requirements.If the required distance is greater than the available distance, the airplane weight must be reduced until distance required is less than or equal to distance available.

TAKEOFF CORRECTIONS – FlApS 20°

If the runway has a gradient and/or the airplane anti-ice system is on, the following correction factors must be applied to the distances and V1 speeds.

rUnWaY Gradient

WeiGHt ranGe — poUnds

23,000 - 18,000 V1 *

17,999 - 15,000 V1 *

2% Uphill Use Vr Use Vr

1.5% Uphill add 8 kts add 8 kts

1% Uphill add 4 kts add 4 kts



Anti-ice ON add 3 kts add 3 kts

* If adjusted V1 is greater than VR use Vr for V1.

�Note:� For contaminated runway takeoff data, see AFM Section VII


Flight Planning


DATA FOR WET, SlUSH, SNOW AND ICE COVERED rUnWaYs

The following information is considered the most accurate and practical guidance material available for adverse runway operations. This advisory information is not FAA approved.

performance

The takeoff field length and landing distance tables presented in Section IV are based on smooth, dry, hard surfaced runways. For takeoffs and landings on precipitation covered runways, use the following tables and correction factors. The tables with thrust reversers present data for wet and ice covered runways.

�Wa�n�ne:� These distances and correction factors for wet and adverse runway conditions are approximate and are to be considered minimums, as actual runway conditions may require distances greater than those determined.

definitions

Runway Contaminated by Compacted Snow:

A runway is considered contaminated by compacted snow when covered by snow which has been compressed into a solid mass which resists further compression and will hold together or break into lumps if picked up.

Runway Contaminated by Standing Water, Slush or loose Snow:

A runway is considered contaminated when more than 25% of the runway surface area (whether in isolated areas or not) within the required length and width being used, is covered by surface water more than 3 millimeters (0.125 inch) deep, or by slush, or loose snow, equivalent to more than 3 millimeters (0.125 inch) of water.

Runway Contaminated by Wet Ice:

A runway surface condition where braking action is expected to be very low, due to the presence of wet ice.

Wet Runway:

A runway is considered wet when there is sufficient moisture on the surface to appear reflective, but without significant areas of standing water.

Flight Planning


takeoff field lenGtH- feet FlApS 7°drY

rUnWaY no

tHrUst reVersers

anti-ice off

adVerse rUnWaY conditions(NO THRUST REVERSERS, All WINDS, 15 FT SCREEN HEIGHT, ANTI-ICE OFF)

Water coVered rUnWaY - incHes

slUsH coVered rUnWaY - incHes

snoW incHes

compact snoW Wet

ice0.125 0.2 0.3 0.125 0.2 0.3 1

2400 4600 4400 4400 4600 4500 4400 4600 3600 84002600 5150 4950 4850 5150 5000 4850 5050 3950 94002800 5700 5500 5300 5700 5500 5300 5500 4300 104003000 6250 6000 5750 6200 5950 5700 5900 4600 115003200 6800 6500 6200 6700 6400 6100 6300 4900 128003400 7300 6950 6600 7200 6850 6500 6700 5200 138003600 7800 7400 7000 7700 7300 6900 7100 5500 150003800 8250 7850 7450 8100 7700 7300 7450 5700 184004000 8700 8300 7900 8500 8100 7700 7800 5900 178004200 9150 8700 8250 8900 8500 8100 8150 61504400 9600 9100 8600 9300 8900 8500 8500 64004600 10000 9450 9000 9650 9250 8850 8850 66004800 10400 9800 9400 10000 9600 9200 9200 68005000 10700 10200 9750 10400 10000 9550 9500 70505200 11000 10600 10100 10800 10400 9900 9800 73005400 11400 10950 10450 11150 10750 10200 10150 75005600 11800 11300 10800 11500 11100 10500 10500 77005800 12150 11650 11150 11850 11450 10900 10850 79006000 12500 12000 11500 12200 11800 11300 11200 81006200 12850 12300 11850 12550 12150 11650 11500 83006400 13200 12600 12200 12900 12500 12000 11800 85006600 13550 12950 12550 13250 12850 12350 12100 87006800 13900 13300 12900 13600 13200 12700 12400 89007000 14200 13600 13200 13900 13500 13050 12700 91007200 14500 13900 13500 14200 13800 13400 13000 93007400 14800 14250 13850 14500 14150 13700 13350 95007600 15100 14600 14200 14800 14500 14000 13700 97007800 15400 14900 14500 15100 14750 14350 13950 99008000 15700 15200 14800 15400 15000 14700 14200 101008200 16000 15500 15100 15700 15300 15000 14500 103008400 16300 15800 15400 16000 15600 15300 14800 105008600 16150 15650 16250 15900 15650 15100 106508800 16500 15900 16500 16200 16000 15400 108009000 16200 16450 16250 110009200 16500 16700 16500 112009400 16700 16800 114009600 16900 17100 116009800 1180010000 1200010200 1215010400 1230010600 1250010800 1270011000 1285011200 1300011400 1315011600 1330011800 1350012000 1370012200 1385012400 1400012600 1415012800 1430013000 1445013200 1460013400 1480013600 1495013800 15100

Flight Planning


takeoff field lenGtH- feet FlApS 20°drY

rUnWaY no

tHrUst reVersers

anti-ice off

adVerse rUnWaY conditions(NO THRUST REVERSERS, All WINDS, 15 FT SCREEN HEIGHT, ANTI-ICE OFF)



snoW incHes compact

snoWWet ice

0.125 0.2 0.25 0.125 0.2 2* 12400 4600 4500 4400 4700 4500 4450 4500 3600 83002600 5100 4900 4800 5100 4900 4900 4900 3950 90502800 5600 5300 5250 5500 5300 5300 5300 4300 98003000 6100 5750 5700 6000 5750 5700 5750 4600 107503200 600 6200 6150 6500 6200 6100 6200 4900 117003400 7050 6650 6600 7000 6650 6500 6600 5150 126003600 7500 7100 7000 7500 7100 6950 7000 5400 135003800 7950 7550 7450 7850 7500 7350 7350 5650 144004000 8400 8000 7900 8200 7900 7700 7700 5900 153004200 8750 8350 8300 8600 8250 8050 8000 61504400 9100 8700 8700 9000 8600 8450 8300 64004600 9450 9100 9050 9350 9000 8800 8650 66004800 9800 9500 9400 9700 9400 9200 9000 68005000 10150 9850 9750 10050 9750 9500 9300 70005200 10500 10200 10100 10400 10100 9900 9600 72005400 10850 10550 10450 10700 10450 10200 9950 74005600 11200 10900 10800 11000 10800 10550 10300 76005800 11550 11250 11100 11350 11150 10900 10600 78006000 11900 11600 11500 11700 11500 11250 10900 80006200 12250 11950 11800 12050 11800 11600 11250 82006400 12600 12300 12100 12400 12100 11950 11600 84006600 12950 12600 12450 12700 12450 12300 11900 86006800 13300 12900 12750 13000 12800 12600 12200 88007000 13650 13250 13100 13350 13100 12900 12500 90007200 14000 13600 13400 13700 13400 13300 12800 92007400 14300 13900 13700 14000 13700 13600 13100 94007600 14600 14200 14050 14300 14000 13950 13400 96007800 14900 14500 14350 14600 14300 14250 13700 98008000 15200 14800 14700 14900 14600 14600 14000 100008200 15500 15050 14950 15250 14900 14900 14250 102008400 15800 15300 15300 15600 15200 15200 14500 104008600 16100 15600 15600 15900 15500 106008800 16400 15900 15900 16200 15800 108009000 16700 16150 16200 16500 16050 110009200 17000 16400 16800 16300 112009400 114009600 116009800 1180010000 1200010200 1220010400 1240010600 1260010800 1280011000 1300011200 1320011400 1345011600 1370011800 1390012000, 1410012200 1430012400 1450012600 1470012800 1490013000 15150

* Takeoffs should not be attempted in 0.25 inches or more of slush at altitudes

greater than 8000 ft.

Flight Planning


landinG distance - feet FlApS 20°

airspeed - VrefdrY

rUnWaY WitHoUt tHrUst

reVersers

adVerse rUnWaY conditions(NO THRUST REVERSERS, WITHOUT TAIlWINDS, 50 FT SCREEN HEIGHT)

Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2

1600 1850 2750 2700 2650 2600 2550 2850 2750 2700 2650 2600 2850 2750 2250 5150

1800 2150 3300 3150 3050 3000 2900 3300 3250 3100 3000 2900 3300 3200 2600 6600

2000 2450 3850 3650 3550 3350 3250 3850 3700 3550 3450 3300 3800 3700 2950 8400

2200 2750 4400 4150 4000 3800 3650 4350 4150 4000 3850 3700 4300 4200 3300 10400

2400 3050 5000 4700 4500 4200 4050 4900 4650 4400 4250 4100 4850 4700 3650 14400

2600 3350 5600 5250 4950 4700 4450 5450 5200 4900 4700 4500 5350 5200 4000

2800 3650 6200 5850 5450 5150 4900 6050 5700 5300 5150 4900 5900 5650 4300

3000 4000 6800 6400 6000 5600 5350 6650 6250 5850 5550 5350 6400 6100 4650

3200 4250 7550 6950 6500 6100 5850 7250 6800 6300 000 5750 6900 6550 4950

3400 4550 8200 7500 7000 6550 6300 7850 7350 6800 6500 6200 7400 7000 5250

3600 4900 8850 8100 7550 7050 6800 8400 7900 7300 6950 6650 7900 7400 5600

3800 5200 9450 8650 8100 7550 7300 9050 8450 7850 7450 7100 8400 7850 5900

4000 5500 10050 9250 8650 8100 7800 9600 9050 8350 7950 7600 8850 8250 6200

4200 5850 10650 9850 9200 8650 8300 10200 9600 8900 8450 8050 9350 8650 6500

4400 6150 11200 10450 9750 9150 8700 10750 10150 9450 8900 8500 9800 9050 6750

4600 6450 11850 11000 10250 9650 9200 11350 10650 9950 9400 8950 1250 9450 7000

4800 6750 12400 11600 10800 10200 9650 11900 11250 10450 9850 9400 10650 9800 7200

5000 7050 12950 12200 11300 10650 10150 12500 11750 10950 10350 9850 11050 10250 7400

5200 7400 13500 12700 11800 11150 10550 13000 12300 11450 10800 10300 11550 10650 7600

5400 7700 14050 13250 12300 11650 11000 13600 12850 11950 11300 10750 12050 11100 7750

5600 8000 14600 13750 12850 12100 11450 14100 13350 12450 11750 11150 12500 11500 7950

5800 8300 15100 14300 13350 12600 11900 14650 13850 12950 12200 11600 13000 11950 8100

6000 8600 15700 14800 13800 13050 12350 15150 14350 13400 12650 12000 13450 12400 8300

6200 8950 16200 1300 14350 13500 12750 15650 14900 13900 13100 12450 13950 12800 8450

6400 9250 16750 15800 14800 13950 13200 16250 15350 14350 13550 12850 14450 13250 8600

6600 9550 17050 16250 15250 14400 13600 16700 15850 14800 14000 13250 14950 13700 8700

�Note:� The published limiting maximum tailwind component for this airplane is 10 Kts: however Cessna does not recommend landings on precipitation-covered runways with any tailwind component. If a tailwind landing cannot be avoided, multiply the above data by the following factor:

Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2tailWind factor 1.02 1.08 1.06 1.05 1.05 1.05 1.07 1.05 1.05 1.05 1.05 1.06 1.05 1.06 *

* landings with any tailwind should not be attempted on wet ice.

Flight Planning


landinG distance - feet FlApS 20°

airspeed - Vref+10

drY

rUnWaY WitHoUt tHrUst

reVersers

adVerse rUnWaY conditions (NO THRUST REVERSERS, WITHOUT TAIlWINDS, 50 FT SCREEN HEIGHT)

Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2

1600 2200 3150 3150 3050 3000 2950 3300 3250 3150 3050 3000 3350 3200 2600 5750

1800 2550 3800 3700 3550 3400 3300 3800 3700 3600 3500 3400 3850 3750 3000 74002000 2900 4500 4300 4050 3900 3750 4400 4200 410D 3950 3800 4400 4300 3400 94002200 3250 5150 4900 4600 4400 4200 5000 4800 4650 4400 4250 5000 4800 3750 11950

2400 3600 5900 5550 5200 4950 4700 5700 5400 5150 4900 4700 5600 5300 4150 15300

2600 4000 6550 6200 5750 5500 5200 6400 6050 5700 5400 5200 6150 5800 4500

2800 4350 7300 6850 6400 6050 5750 7100 6700 6250 5950 5650 6700 6350 49003000 4700 8000 7500 7050 6600 6250 7800 7350 6850 6450 6150 7300 6850 53003200 5050 8700 8150 7700 7200 6800 8500 8000 7400 7000 6650 7900 7350 56503400 5400 9450 8800 8300 7750 7400 9150 8600 8000 7550 7200 8450 7850 6000

3600 5750 10150 9500 8900 8350 7900 9850 9200 8600 8100 7700 9000 8350 6350

3800 6100 10950 10150 9550 8900 8450 10550 9850 9200 8650 8250 9550 8850 67004000 6500 11700 10850 10100 9500 9000 11300 10550 9750 9200 8750 10100 9300 70504200 6850 12400 11550 10750 10050 9550 12000 11200 10350 9800 9300 10700 9800 7350

4400 7200 13100 12200 11350 10650 10100 12700 11850 10950 10300 9800 11250 10300 7700

4600 7550 13750 12800 11900 11250 10650 13350 12500 11550 10900 10350 11750 10800 8000

4800 7900 14400 13400 12500 11800 11150 14000 13100 12150 11400 10900 12250 11300 8250

5000 8300 15050 14000 13050 12350 11700 14650 13750 12750 11950 11400 12750 11750 8500

5200 8650 15650 14600 13650 12900 12200 15300 14350 13300 12500 11950 13300 12200 86505400 9050 15200 14200 13450 12800 15900 14900 13900 13100 12450 13900 12650 8850

5600 9400 15800 14750 14000 13300 15450 14450 13650 12950 14400 13100 9000

5800 9800 15350 14550 13800 16000 15000 14200 13450 15000 13550 9100

6000 10200 15900 15100 14300 15550 14700 13950 15550 14000 9150

6200 10600 15600 14800 15250 14400 14450 9200

6400 10950 15300 14900 14900 9300


Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2tailWind factor 1.01 1.06 1.04 1.03 1.02 1.02 1.03 1.04 1.03 1.02 1.02 1.04 1.03 1.08 *


Flight Planning


landinG distance - feet flaps fUll

airspeed - Vref

drY rUnWaY WitHoUt tHrUst

reVersers

adVerse rUnWaY conditions (NO THRUST REVERSERS, WITHOUT TAIlWINDS, 50 FT SCREEN HEIGHT)

Wet rUnWaY



snoW incHes compact

snoWWet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2

1600 1900 2850 2800 2700 2600 2550 2950 2850 2800 2750 2650 3000 2850 2300 5500

1800 2150 3300 3250 3100 2950 2900 3400 3350 3250 3100 3000 3450 3350 2650 7050

2000 2450 3750 3700 3550 3350 3250 3900 3800 3650 3500 3350 3950 3800 3000 9100

2200 2750 4300 4150 3950 3750 3600 4450 4300 4050 3900 3750 456 4300 3350 12200

2400 3100 4900 4700 4400 14200 4000 4900 4750 4450 4300 4100 4950 4750 3700

2600 3400 5500 5250 4900 4600 4450 5400 5250 4900 4700 4500 5500 5150 4000

2800 3700 6100 5750 5350 5050 4850 5950 5700 5350 5100 4900 6000 5600 4350

3000 4000 6700 6300 5850 5550 5350 6550 6250 5800 5550 5350 6450 6050 4700

3200 4300 7300 6850 6300 6050 5800 7100 6750 6300 6000 5750 6900 6500 5000

3400 4600 7900 7400 6800 6500 6250 7700 7250 6750 6450 6200 7400 6950 5300

3600 4950 8500 7900 7300 7000 6700 8250 7750 7250 6900 6650 7850 7350 5600

3800 5200 9100 8450 7850 7450 7200 8850 8300 7750 7400 7100 8300 7750 5900

4000 5550 9600 8950 8350 7950 7650 9350 8850 8250 7800 7550 8750 8200 6200

4200 5850 10150 9550 8900 8450 8100 9950 9350 8700 8300 8000 9250 8600 6450

4400 6150 10700 10100 9400 8900 8500 10500 9900 9250 8750 8450 9700 9050 6650

4600 6450 11300 10600 9900 9350 8950 11050 10400 9 700 9200 8800 10150 9500 6900

4800 6750 11850 11100 10350 9850 9400 11550 10900 10150 9650 9250 10600 9900 7100

5000 7050 12400 11650 10900 10350 9850 12100 11250 10700 10050 9700 11050 10300 7300

5200 7350 12950 12150 11350 10750 10250 12650 11950 11150 10550 10100 11500 10700 7500

5400 7650 13450 12650 11900 11250 10700 13150 12450 11600 11000 10500 11950 11100 7700

5600 7950 13950 13150 12300 11650 11100 13650 12900 12100 11450 10900 12350 11500 7850

5800 8250 14450 13650 12850 12050 11500 14150 13450 12550 11900 11350 12800 11900 8000

6000 8550 14950 14100 13300 12450 11850 14700 13950 13000 12300 11750 13200 12250 8150

6200 8800 15400 14550 13750 12850 12250 15150 14450 13450 12700 12200 13650 12650 8300

6400 9100 15800 15000 14250 13250 12600 15700 14900 13900 13150 12550 14050 13050 8400

6600 9400 16200 16400 14650 13650 12950 16250 15350 14350 13600 12900 14450 13450 8500


Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2tailWind factor 1.04 1.08 1.07 1.05 1.06 1.06 1.06 1.06 1.04 1.03 1.03 1.05 1.07 1.06 *


Flight Planning


landinG distance - feet flaps fUll

airspeed - Vref + 10

drY rUnWaY WitHoUt tHrUst

reVersers

adVerse rUnWaY conditions(NO THRUST REVERSERS, WITHOUT TAIlWINDS, 50 FT SCREEN HEIGHT)

Wet rUnWaY



snoW incHes compact

snoWWet ice

0.125 0.2 0.3 0.4 .5 0.125 0.2 0.3 0.4 0.5 1 21600 2250 3300 3200 3100 3000 2900 3350 3250 3200 3100 3000 3400 3350 2700 6050

1800 2600 3900 3750 3550 3400 3300 3850 3750 3650 3500 3400 3900 3800 3100 80002000 2950 4500 4300 4050 3900 3750 4450 4300 4150 4000 3850 4500 4350 3500 10550

2200 3300 5150 4850 4600 4400 4200 5050 4850 4650 4450 4300 5000 4850 3900 14200

2400 3650 5800 5500 5200 4900 4700 5650 5450 5200 4900 4700 5600 5400 4250

2600 4000 6550 6100 5750 5350 5150 6300 6100 5700 5400 5150 6200 5900 4650

2800 4350 7250 6750 6300 5850 5650 7000 6700 6200 5850 5600 6750 6400 5000

3000 4700 7900 7400 6850 6400 6150 7700 7300 6750 6350 6100 7300 6900 5350

3200 5100 8600 8000 7400 6950 6700 8350 7900 7300 6900 6600 7850 7400 5700

3400 5450 9300 8600 8000 7500 7200 9000 8500 7850 7400 7100 8400 7850 6050

3600 5800 10000 9300 8550 8100 7750 9650 9100 8400 7900 7650 8950 8350 6400

3800 6100 10650 9950 9150 8650 8300 10300 9700 8900 8500 8150 9500 8850 6750

4000 6400 11300 10550 9700 9200 8800 10950 10300 9500 9000 8700 10050 9300 7100

4200 6800 11950 11150 10350 9750 9300 11550 10850 10050 9550 9150 10600 9800 7450

4400 7150 12600 11750 10900 10300 9850 12150 11450 10600 10100 9650 11150 10300 7750

4600 7500 13200 12350 11500 10850 10350 12800 12000 11200 10650 10150 11700 10750 8100

4800 7900 13850 12950 12050 11350 10800 13400 12550 11800 11150 10650 12200 11200 8450

5000 8250 14500 13550 12600 11900 11350 13950 13150 12400 11700 11150 12750 11700 8750

5200 8600 15100 14100 13150 12400 11850 14600 13750 13000 12200 11650 13300 12100 9100

5400 9000 15700 14700 13700 12950 12350 15200 14350 13600 12700 12150 13800 12600 9450

5600 9350 15250 14250 13450 12850 15750 14900 14150 13200 12600 14300 13050 9750

5800 9750 15850 14800 13950 13300 15500 14700 13750 13100 14800 13500 10100

6000 10100 15300 14450 13800 15250 14200 13550 15300 13900 10400

6200 10500 15800 14950 14300 15800 14700 14000 15800 14350 10700

6400 10900 15450 14750 15200 14450 14800 11000


Wet rUnWaY



snoW incHes

compact snoW

Wet ice

0.125 0.2 0.3 0.4 0.5 0.125 0.2 0.3 0.4 0.5 1 2tailWind factor 1.02 1.07 1.06 1.04 1.05 1.03 1.08 1.06 1.04 1.06 1.03 1.04 1.02 1.00 *


Flight Planning


tHrUst reVerser precipitation

takeoff coVered rUnWaYstakeoff field lenGtH

drY Hard sUrface WitHoUt

tHrUst reVerser

Wet concrete WitH tHrUst

reVerser

ice WitH tHrUst

reVerser2600 3120 44002800 3375 47203000 3620 50203200 3860 52953400 4090 55453600 4320 57703800 4550 59854000 4775 61904200 4995 63854400 5215 65704600 5430 67654800 5635 69505000 5840 71405200 6040 73205400 6235 75055600 6415 76955800 6585 78556000 6735 80106200 6865 81306400 6980 82456600 7100 83656800 7215 8480 7000 7335 8600

tHrUst reVerser landinG precipitation coVered rUnWaYs

landinG distancedrY Hard sUrface

WitHoUt tHrUst reVerser

Wet concrete WitH tHrUst

reVerser

ice WitH tHrUst

reVerser2200 2350 32302400 2630 36902600 2890 40502800 3130 43803000 3360 46703200 3590 49203400 3810 51303600 4020 53103800 4240 54704000 4450 56154200 4660 57504400 4860 5880

Flight Planning


GroUnd deice/anti-ice operations

During cold weather operations, flight crews are responsible for ensuring the airplane is free of ice contaminants.

Ground icing may occur whenever there is high humidity with temperatures of +10°C or colder. Type I deice, and Type II or Type IV anti-ice fluids may be used sequentially to ensure compliance with FAA regulations (clean wing concept) requiring critical component airframe deicing and anti-icing.

�Note:� It is recommended that flight crews re-familiarize themselves season-ally with the following publications for expanded deice and anti-ice procedures:

� Cessna Maintenance Manual Chapter 12. � FAA Advisory Circular AC 120-58 (large aircraft), dated

September 30, 1992 or later. � FAA Advisory Circular AC 135-17 (small aircraft), dated

December 14, 1994 or later. � Cessna Citation Service letter 560-30-08, dated May 29,

1998 or later.

DEICING/ANTI-ICING pROCEDURES (TYpE I, TYpE II, AND TYpE IV FlUIDS)

ONE STEp DEICING — Type I fluid is used to remove ice, slush and snow from the airplane prior to departure, and to provide minimal anti-icing protection as provided in the Type I holdover timetable (refer to applicable service letter).

TWO STEp DEICE/ANTI-ICE — May be used to ensure the airplane remains clean after deicing. Type II or Type IV fluid is used to provide longer term anti-icing protection as provided in the Type II or Type IV holdover timetable (refer to applicable service letter).

�CWuonN�e: Type I, Type II, and Type IV fluids are not compatible and may not be mixed. Additionally, most manufacturers prohibit mixing of brands within a type.

Flight Planning


primarY trim takeoff settinG Vs airplane center-of-GraVitY


Flight Planning


sea leVel Zero Wind or Gradient takeoff

FlApS 7° Anti-Ice Systems ONlH & rH enGine Bleed air off*

T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 91.8 92.5 94.3 96.1 97.8 99.6 98.0 96.091.8 92.5 94.3 96.1 97.8 ---- ---- ----

S/E Climb90.5 91.2 92.8 94.7 96.5 97.5 95.6 93.690.5 91.4 93.2 95.0 95.4 ---- ---- ----

23.0 V1130 130 130 130 130 130 131 132130 130 131 131 131 ---- ---- ----

Venr Vr 130 130 131 131 131 131 131 132 165.0 V2 143 143 143 143 143 143 143 143

Vref rWY4430 4520 4690 4860 5040 5320 5860 6860

143.0 4873 4972 5159 5346 5544 ---- ---- ----

22.0 V1128 128 127 127 127 127 128 129128 128 128 128 128 ---- ---- ----

Venr Vr 128 128 128 128 128 128 128 129165.0 V2 141 141 141 141 141 141 141 141Vref rWY

4120 4190 4350 4500 4660 4910 5400 6270141.0 4532 4609 4785 4950 5126 ---- ---- ----

21.0 V1126 126 126 126 125 125 125 126

127 127 127 127 127 ---- ---- ----Venr Vr 127 127 127 127 127 126 126 126165.0 V2 140 140 140 140 140 139 138 138Vref rWY

3910 3980 4120 4270 4410 4570 4960 5720138.0 4301 4378 4532 4697 4851 ---- ---- ----

20.0 V1125 125 124 124 124 123 121 123

126 126 126 126 126 ---- ---- ----Venr Vr 126 126 126 126 126 125 123 123165.0 V2 140 139 139 139 139 138 136 136Vref rWY

3710 3770 3900 4040 4180 4320 4540 5210135.0 4081 4147 4290 4444 4598 ---- ---- ----

19.0 V1123 123 123 123 122 121 120 120125 125 125 125 124 ---- ---- ----

Venr Vr 125 125 125 125 125 124 122 120165.0 V2 139 139 139 139 139 137 135 133Vref rWY

3500 3570 3690 3820 3950 4080 4270 4740132.0 3850 3927 4059 4202 4345 ---- ---- ----

18.0 V1121 121 121 121 120 119 118 116123 123 123 123 122 ---- ---- ----

Venr Vr 124 124 124 124 124 123 120 117165.0 V2 138 138 138 138 137 136 133 129Vref rWY

3290 3350 3470 3590 3700 3830 3990 4260129.0 3619 3685 3817 3949 4070 ---- ---- ----

* For bleed air on increase take-off distance by 100 ft.


take

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Flight Planning


takeoff Zero Wind or Gradient sealeVel

Anti-Ice Systems on flaps 20°lH & rH enGine Bleed air off*

T.O. Gross

Weight X

1,000

Temp C -25 -20 -10 0 10 20 30 4091.8 92.5 94.3 96.1 97.8 99.6 98.0 96.0

T/O power 91.8 92.5 94.3 96.1 97.8 ---- ---- ----S/E Climb 90.5 91.2 92.8 94.7 96.5 97.5 95.6 93.6

90.5 91.4 93.2 95.0 95.4 ---- ---- ----

23.0 V1125 125 125 125 125 124 124127 127 127 127 127 ---- ---- ----

Venr Vr 127 127 127 127 127 126 126 -- 165 V2 137 137 137 137 137 136 135 --

Vref rWY4350 4440 4600 4780 4950 5220 5770 --

143 4785 4884 5060 5258 5445 ---- ---- ----

22.0 V1123 123 123 123 123 122 122 123125 125 125 125 125 ---- ---- ----

Venr Vr 125 125 125 125 125 125 123 123165 V2 135 135 135 135 135 134 133 133

Vref rWY3960 4030 4180 4330 4480 4690 5020 5690

141 4356 4433 4598 4763 4928 ---- ---- ----

21.0 V1121 121 121 121 121 120 120 120123 123 123 123 123 ---- ---- ----

Venr Vr 123 123 123 123 123 123 122 121165 V2 134 134 134 134 133 133 132 130

Vref rWY3720 3790 3920 4070 4210 4390 4690 5230

138 4092 4169 4312 4477 4631 ---- ---- ----

20.0 V1121 121 121 121 121 120 120 120123 123 123 123 123 ---- ---- ----

Venr Vr 123 123 123 123 123 123 122 121165 V2 134 134 134 134 133 133 132 130

Vref rWY3720 3790 3920 4070 4210 4390 4690 5230

135 4092 4169 4312 4477 4631 ---- ---- ----

19.0 V1117 116 116 116 116 116 115 115119 118 118 118 118 ---- ---- ----

Venr Vr 120 120 120 120 120 119 118 116165 V2 130 130 130 130 130 129 128 126

Vref rWY3370 3430 3550 3680 3800 3990 4290 4720

132 3707 3773 3905 4048 4180 ---- ---- ----

18.0 V1114 114 114 114 113 113 112 112116 116 116 116 115 ---- ---- ----

Venr Vr 118 118 118 118 118 117 116 114165 V2 128 128 128 128 128 128 126 124

Vref rWY2840 3080 3190 3300 3410 3540 3760 4100

129 3124 3388 3509 3630 3751 ---- ---- ----



take

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Flight Planning


1,000 FT Zero Wind or Gradient takeoff

FlApS 7° Anti-Ice Systems onlH & rH enGine Bleed air off*

T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 93.0 93.9 95.6 97.4 99.2 99.8 98.2 96.393.0 93.9 95.6 97.4 98.9 --- --- ---

S/E Climb 91.4 92.2 94.0 95.7 97.5 97.5 95.6 93.292.0 92.6 94.4 96.0 95.4 --- --- ---

23.0 V1130 130 130 130 130 130 131 132130 131 131 131 131 --- --- ---

Venr Vr 130 131 131 131 131 131 131 132 165.0 V2 143 143 143 143 143 143 143 143

VrefrWY

4590 4680 4850 5040 5220 5600 6290 7420 143 5049 5148 5335 5544 5742 --- --- ---

22.0 V1127 127 127 127 127 127 128 129128 128 128 128 128 --- --- ---

Venr Vr 128 128 128 128 128 128 129 129165 V2 141 141 141 141 141 141 141 141

VrefrWY

4260 4340 4500 4660 4820 5160 5790 6780141 4686 4774 4950 5126 5302 --- --- ---

21.0 V1126 126 126 125 125 124 125 127127 127 127 127 127 --- --- ---

Venr Vr 127 127 127 127 127 125 126 127165.0 V2 140 140 140 140 140 138 138 138Vref

rWY4040 4120 4270 4410 4560 4750 5310 6180

138 4444 4532 4697 4851 5016 --- --- ---

20.0 V1125 125 125 125 124 122 122 124126 126 126 126 126 --- --- ---

Venr Vr 126 126 126 126 126 124 123 124165 V2 140 139 139 139 139 137 136 136

VrefrWY

3830 3900 4040 4180 4320 4480 4850 5610135 4213 4290 4444 4598 4752 --- --- ---

19.0 V1123 123 123 122 122 121 119 121125 125 125 124 124 --- --- ---

Venr Vr 125 125 125 125 125 123 120 121165 V2 139 139 139 139 138 137 133 133

VrefrWY

3620 3690 3820 3950 4080 4230 4460 5080132 3982 4059 4202 4345 4488 --- --- ---

18.0 V1121 121 121 120 120 119 117 117123 123 123 122 122 --- --- ---

Venr Vr 124 124 124 124 124 122 119 117165 V2 138 138 138 137 137 135 132 129

Vref rWY3400 3460 3580 3710 3830 3960 4160 4570

129 3740 3806 3938 4081 4213 --- --- ---



take

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Flight Planning


takeoff Zero Wind or Gradient 1,000 FT


T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 93.0 93.9 95.6 97.4 99.2 99.8 98.2 96.393.0 93.9 95.6 97.4 98.9 --- --- ---

S/E Climb 91.4 92.2 94.0 95.7 97.5 97.5 95.6 93.292.0 92.6 94.4 96.0 95.4 --- --- ---

23.0 V1125 125 125 125 124 124

127 127 127 127 127 --- --- ---Venr Vr 127 127 127 127 127 126 126 --

165.0 V2 137 137 137 136 136 136 135 --Vref rWY

4350 4440 4600 4780 4950 5220 5770 -- 143 4785 4884 5060 5258 5445 --- --- ---

22.0 V1123 123 123 123 123 122 122124 124 124 124 124 --- --- ---

Venr Vr 124 124 124 124 124 123 123 --165 V2 135 135 135 135 135 134 133 --

Vref rWY4090 4170 4330 4490 4650 4900 5330 --

141 4499 4587 4763 4939 5115 --- --- ---

21.0 V1121 121 121 121 121 120 119 120123 123 123 123 123 --- --- ---

Venr Vr 123 123 123 123 123 123 121 121165.0 V2 134 134 134 133 133 133 131 130Vref rWY

3840 3920 4060 4210 4360 4580 4950 5610138 4225 4312 4466 4631 4796 --- --- ---

20.0 V1119 119 119 118 118 118 117 117121 121 121 120 120 --- --- ---

Venr Vr 122 122 122 122 122 121 119 118165 V2 132 132 132 132 132 131 129 128

Vref rWY3600 3670 3800 3940 4070 4280 4610 5140

135 3960 4037 4180 4334 4477 --- --- ---

19.0 V1117 116 116 116 116 116 115 115119 118 118 118 118 --- --- ---

Venr Vr 120 120 120 120 120 119 118 116165 V2 130 130 130 130 130 129 128 126

Vref rWY3370 3430 3550 3680 3800 3990 4290 4720

132 3707 3773 3905 4048 4180 --- ---- ---

18.0 V1114 114 114 113 113 113 112 112116 116 116 115 115 --- --- ---

Venr Vr 118 118 118 118 118 117 115 114165 V2 128 128 128 128 128 127 125 123

VrefrWY

3120 2990 3290 3410 3520 3690 3950 4330129 3432 3289 3619 3751 3872 --- --- ---



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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 94.0 95.0 96.4 98.4 100.2 99.6 --- ---94.0 95.0 96.4 98.4 98.8 --- --- ---

S/E Climb 92.4 93.2 95.0 96.8 98.6 --- --- ---93.3 94.1 95.2 97.7 95.4 --- --- ---

23.0 V1130 130 130 130 129 130 132 132130 131 131 131 131 --- --- ---

Venr Vr 130 131 131 131 131 131 132 132 165 V2 143 143 143 143 143 143 143 143

Vref rWY4750 4840 5030 5220 5410 5930 6770 8040

143 5225 5324 5533 5742 5951 --- --- ---

22.0 V1127 127 127 127 126 127 129 129128 128 128 128 128 --- --- ---

Venr Vr 128 128 128 128 128 128 129 129165 V2 141 141 141 141 141 141 141 141

Vref rWY4400 4490 4650 4820 4990 5460 6210 7340

141 4840 4939 5115 5302 5489 --- --- ---

21.0 V1126 126 125 125 125 124 126 127127 127 127 127 127 --- --- ---

Venr Vr 127 127 127 127 126 125 126 127165 V2 140 140 140 140 140 138 138 138

Vref rWY4180 4260 4410 4570 4720 5020 5690 6680

138 4598 4686 4851 5027 5192 --- --- ---

20.0 V1124 124 124 124 123 122 123 124126 126 126 126 123 --- --- ---

Venr Vr 126 126 126 126 123 123 123 124165 V2 139 139 139 139 139 136 136 136

Vref rWY3960 4030 4180 4320 4470 4660 5200 6060

135 4356 4433 4598 4752 4917 --- --- ---

19.0 V1123 123 122 122 122 120 119 121125 125 124 124 124 --- --- ---

Venr Vr 125 125 125 125 125 122 120 121165 V2 139 139 139 138 138 136 133 133

Vref rWY3740 3810 3950 4090 4220 4390 4730 5470

132 4114 4191 4345 4499 4642 --- --- ---

18.0 V1121 121 120 120 120 118 116 117123 123 122 122 122 --- --- ---

Venr Vr 124 124 124 124 124 121 118 117165 V2 138 138 137 137 137 134 131 129

Vref rWY3510 3580 3700 3830 3960 4110 4340 4900

129 3861 3938 4070 4213 4356 --- --- ---

* For bleed air on increase take-off distance by 100 ft.Citation VII with TFE731-4 Engines

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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 94.0 95.0 96.4 98.4 100.2 99.6 --- ---94.0 95.0 96.4 98.4 98.8 --- --- ---

S/E Climb 92.4 93.2 95.0 96.8 98.6 --- --- ---93.3 94.1 95.2 97.7 95.4 --- --- ---

23.0 V1125 125 125 125 124 124 125127 127 127 127 126 --- --- ---

Venr Vr 127 127 127 127 127 126 126 -- 165 V2 137 137 137 136 136 135 135 --

Vref rWY4510 4600 4770 4950 5130 5480 6180

143 4961 5060 5247 5445 5643 --- --- ---

22.0 V1123 123 123 123 122 122 122125 125 125 125 124 --- --- ---

Venr Vr 125 125 125 125 125 124 123 --165 V2 135 135 135 135 135 134 133 --

Vref rWY4240 4320 4480 4650 4810 5130 5200

141 4664 4752 4928 5115 5291 --- --- ---

21.0 V1121 121 121 120 120 120 119 120123 123 123 122 122 --- --- ---

Venr Vr 123 123 123 123 123 122 121 121165 V2 134 134 133 133 133 132 130 130

Vref rWY3980 4050 4200 4360 4510 4790 5250 6010

138 4378 4455 4620 4796 4961 --- --- ---

20.0 V1119 119 118 118 118 117 117 118121 121 120 120 120 --- --- ---

Venr Vr 122 122 122 122 122 120 119 118165 V2 132 132 132 132 132 130 129 128

Vref rWY3730 3800 3940 4070 4220 4470 4870 5500

135 4103 4180 4334 4477 4642 --- --- ---

19.0 V1116 116 116 116 116 115 115 115118 118 118 118 118 --- --- ---

Venr Vr 120 120 120 120 120 119 117 116165 V2 130 130 130 130 130 129 127 125

Vref rWY3480 3550 3670 3810 3940 4170 4530 5020

132 3828 3905 4037 4191 4334 --- --- ---

18.0 V1114 114 113 113 113 112 112 112116 116 115 115 115 --- --- ---

Venr Vr 118 118 118 118 118 116 115 113165 V2 128 128 128 128 128 127 125 123

Vref rWY3230 3290 3410 3530 3650 3850 4160 4570

129 3553 3619 3751 3883 4015 --- --- ---


take

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Flight Planning


3,000 FT Zero Wind or Gradient takeoffFlApS 7° Anti-Ice Systems on

lH & rH enGine Bleed air off*T.O.

Gross Weight

X 1000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 95.3 96.1 98.0 99.4 101.0 99.6 98.0 96.095.3 96.1 98.0 99.4 98.6 --- --- ---

S/E Climb 93.5 94.4 96.1 97.9 99.0 97.6 95.6 93.293.9 94.8 96.7 97.2 95.5 --- --- ---

23.0 V1130 130 130 129 129 129 130 --

130 130 130 131 131 --- --- ---Venr Vr 130 130 130 131 131 131 132 --

165 V2 143 143 143 143 143 143 143 --Vref rWY 4910 5000 5200 5400 5700 6340 7330 --

143 5401 5500 5720 5940 6270 --- --- ---

22.0 V1127 127 127 126 127 128 129 130

128 128 128 128 128 -- -- --Venr Vr 128 128 128 128 128 128 129 130

165 V2 141 141 141 141 141 141 141 141Vref rWY 4560 4640 4820 4990 5250 5840 6700 7970

141 5016 5104 5302 5489 5775 --- -- ---

21.0 V1126 126 125 125 124 124 126 127

127 127 127 127 126 --- --- ---Venr Vr 127 127 127 127 126 125 126 127

165 V2 140 140 140 140 139 138 138 138Vref rWY 4320 4400 4560 4730 4910 5360 6120 7240

138 4752 4840 5016 5203 5401 --- --- ---

20.0 V1124 124 124 124 123 121 123 124

126 126 126 126 125 --- --- ---Venr Vr 126 126 126 126 125 123 123 124

165 V2 140 140 139 139 138 136 136 136Vref rWY

4090 4170 4320 4470 4640 4900 5590 6560 135 4499 4587 4752 4917 5104 --- --- ---

19.0 V1123 122 122 122 121 119 120 121

125 124 124 124 123 --- --- ----Venr Vr 125 125 125 125 124 121 120 121

165 V2 139 139 139 139 138 134 133 133Vref rWY 3870 3940 4080 4230 4380 4580 5080 5910

132 4257 4334 4488 4653 4818 --- --- ---

18.0 V1121 120 120 120 119 117 116 118

123 122 122 122 121 --- --- ---Venr Vr 124 124 124 124 123 120 117 118

165 V2 138 138 138 137 136 133 129 129Vref rWY 3630 3700 3830 3960 4110 4280 4570 5270

129 3993 4070 4213 4356 4521 --- --- ---


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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 95.3 96.1 98.0 99.4 101.0 99.6 98.0 96.095.3 96.1 98.0 99.4 98.6 --- --- ---

S/E Climb 93.5 94.4 96.1 97.9 99.0 97.6 95.6 93.293.9 94.8 96.7 97.2 95.5 --- --- ---

23.0 V1125 125 125 124 124 124127 127 127 126 126 --- --- ---

Venr Vr 127 127 127 127 126 126 -- -- 165 V2 137 137 137 136 136 135 -- --

Vref rWY4660 4760 4940 5120 5370 5840 -- --

143 5126 5236 5434 5632 5907 --- --- ---

22.0 V1123 123 123 122 122 121 122125 125 125 124 124 --- --- ---

Venr Vr 125 125 125 125 125 123 123 --165 V2 135 135 135 135 135 133 133 --

Vref rWY4380 4470 4640 4810 5030 5410 6120 --

141 4818 4917 5104 5291 5533 --- --- ---

21.0 V1121 120 120 120 120 119 120123 122 122 122 122 --- --- ---

Venr Vr 123 123 123 123 123 122 121 --165.0 V2 134 134 134 133 133 131 130 --Vref rWY

4110 4190 4350 4510 4710 5050 5630 --138 4521 4609 4785 4961 5181 --- --- ---

20.0 V1119 118 118 118 118 117 117 118121 120 120 120 120 --- --- ---

Venr Vr 122 122 122 122 121 120 118 118165 V2 132 132 132 132 131 130 128 128

Vref rWY3850 3930 4060 4210 4400 4710 5160 5900

135 4235 4323 4466 4631 4840 --- --- ---

19.0 V1116 116 116 116 116 115 115 115118 118 118 118 118 --- --- ---

Venr Vr 120 120 120 120 119 118 116 116165 V2 130 130 130 130 130 128 126 125

Vref rWY4260 4340 4480 4640 4830 5150 5630 6320

132 4686 4774 4928 5104 5313 --- --- ---

18.0 V1113 113 113 113 113 112 112 112115 115 115 115 115 --- --- ---

Venr Vr 118 118 118 118 117 116 114 113165 V2 128 128 128 128 128 126 124 122

Vref rWY3330 3400 3520 3640 3790 4040 4400 4850

129 3663 3740 3872 4004 4169 --- --- ---


take

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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 96.6 97.6 99.5 100.7 99.0 97.0 98.2 96.396.6 97.6 99.5 100.6 98.9 --- --- ---

S/E Climb 94.8 95.7 97.5 99.3 99.2 97.7 95.8 93.495.3 96.3 98.2 97.3 95.6 --- --- ---

23.0 V1128 128 127 127 128 129 131130 130 129 129 130 --- --- ---

Venr Vr 130 130 130 131 131 131 132 -- 165 V2 143 143 143 143 143 143 143 --

Vref rWY5080 5170 5360 5610 6060 6830 7940

143 5588 5687 5896 6171 6666 --- --- ---

22.0 V1127 127 127 126 127 128 129128 128 128 128 128 --- --- ---

Venr Vr 128 128 128 128 128 129 129 --165 V2 141 141 141 141 141 141 141 --

Vref rWY4720 4800 4980 5170 5580 6280 7250

141 5192 5280 5478 5687 6138 --- --- ---

21.0 V1125 125 125 125 124 125 126 127127 127 127 127 125 --- --- ---

Venr Vr 127 127 127 127 125 126 126 127165 V2 140 140 140 140 138 138 138 138

Vref rWY4470 4550 4720 4900 5130 5730 6610 7860

138 4917 5005 5192 5390 5643 --- --- ---

20.0 V1124 124 124 123 122 122 124 124126 126 126 125 124 --- --- ---

Venr Vr 126 126 126 126 124 123 124 124165 V2 140 140 140 139 137 136 136 136

Vref rWY4230 4310 4470 4630 4840 5260 6000 7110

135 4653 4741 4917 5093 5324 --- --- ---

19.0 V1122 122 122 122 121 119 120 121124 124 124 124 123 --- --- ---

Venr Vr 125 125 125 125 123 120 121 121165 V2 139 139 139 138 136 133 133 133

Vref rWY4000 4080 4220 4380 4560 4800 5450 6400

132 4400 4488 4642 4818 5016 --- --- ---

18.0 V1120 120 120 120 119 116 116 118122 122 122 122 121 --- --- ---

Venr Vr 124 124 124 124 122 119 117 118165 V2 138 138 138 137 135 132 129 129

Vref rWY 3750 3820 3960 4100 4270 4470 4900 5700129 4125 4202 4356 4510 4697 --- --- ---



take

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Flight Planning


takeoff Zero Wind or Gradient 4000 FT


T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 96.6 97.6 99.5 100.7 99.0 97.0 98.2 96.396.6 97.6 99.5 100.6 98.9 --- --- ---

S/E Climb 94.8 95.7 97.5 99.3 99.2 97.7 95.8 93.495.3 96.3 98.2 97.3 95.6 --- --- ---

23.0 V1125 125 124 124 124 124127 127 126 126 126 --- --- ---

Venr Vr 127 127 127 127 126 126 -- -- 165 V2 137 137 137 136 136 135 -- --

Vref rWY4830 4920 5100 5320 5640 6260 -- --

143 5313 5412 5610 5852 6204 --- --- ---

22.0 V1123 123 122 122 122 122125 125 124 124 124 --- --- ---

Venr Vr 125 125 125 125 124 123 -- --165 V2 135 135 135 135 134 133 -- --

Vref rWY4540 4620 4790 4990 5280 5780 -- --

141 4994 5082 5269 5489 5808 --- --- ---

21.0 V1121 120 120 120 120 119 120123 122 122 122 122 --- --- ---

Venr Vr 123 123 123 123 122 121 121 --165.0 V2 134 134 134 133 132 131 130 --Vref rWY

4260 4340 4490 4670 4940 5350 6030 --138 4686 4774 4939 5137 5434 --- --- ---

20.0 V1118 118 118 118 118 117 117 118120 120 120 120 120 --- --- ---

Venr Vr 122 122 122 122 121 119 118 118165 V2 132 132 132 132 131 129 128 128

Vref rWY3980 4050 4200 4370 4610 4980 5530 6340

135 4378 4455 4620 4807 5071 --- --- ---

19.0 V1116 116 116 116 115 115 114 115118 118 118 118 117 --- --- ---

Venr Vr 120 120 120 120 119 117 116 116165 V2 130 130 130 130 129 127 126 125

Vref rWY3720 3790 3920 4080 4300 4630 5070 5770

132 4092 4169 4312 4488 4730 --- --- ---

18.0 V1113 113 113 113 113 112 112 112115 115 115 115 115 --- --- ---

Venr Vr 118 118 118 118 117 115 114 113165 V2 128 128 128 128 127 125 123 122

Vref rWY3450 3510 3630 3780 3970 4260 4650 5200

129 3795 3861 3993 4158 4367 --- --- ---



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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 98.0 99.0 101.2 101.5 101.1 99.8 98.2 96.298.0 99.0 1012.0 100.5 98.9 --- --- ---

S/E Climb 94.9 95.9 97.7 99.5 99.0 97.6 95.5 93.296.0 97.0 99.0 97.2 95.4 --- --- ---

23.0 V1129 129 129 129 130 131 132130 130 131 131 131 --- --- ---

Venr Vr 130 130 131 131 131 132 132 -- 165 V2 143 143 143 143 143 143 143 --

Vref rWY5260 5350 5600 5960 6530 7370 8630 --

143 5786 5885 6160 6556 7183 --- --- ---

22.0 V1127 127 126 126 127 127 129128 128 128 128 128 --- --- ---

Venr Vr 128 128 128 128 128 129 129 --165 V2 141 141 141 141 141 141 141 --

Vref rWY4880 4970 5170 5490 6010 6760 7870 --

141 5368 5467 5687 6039 6611 --- --- ---

21.0 V1125 125 125 124 124 126 127 127127 127 127 126 126 --- --- ---

Venr Vr 127 127 127 126 126 126 127 127165 V2 140 140 140 138 138 138 138 138

Vref rWY4630 4710 4900 5110 5510 6190 7160 8560

138 5093 5181 5390 5621 6061 --- --- ---

20.0 V1124 124 123 123 121 122 124 124126 126 125 125 123 --- --- ---

Venr Vr 126 126 126 125 123 123 124 124165 V2 140 140 139 138 136 136 136 136

Vref rWY4380 4460 4630 4830 5070 5660 6490 7730

135 4818 4906 5093 5313 5577 --- --- ---

19.0 V1122 122 122 121 120 119 121 121124 124 124 123 122 --- --- ---

Venr Vr 125 125 125 124 122 120 121 121165 V2 139 139 139 137 135 133 133 133

Vref rWY4140 4220 4380 4560 4770 5150 5870 6950

132 4554 4642 4818 5016 5247 --- --- ---

18.0 V1120 120 120 119 118 116 117 118122 122 122 121 120 --- --- ----

Venr Vr 124 124 124 123 121 117 117 118165 V2 138 138 137 136 134 130 129 129

Vref rWY3880 3950 4100 4270 4460 4690 5270 6180

129 4268 4345 4510 4697 4906 --- --- ---



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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 98.0 99.0 101.2 101.5 101.1 99.8 98.2 96.298.0 99.0 1012.0 100.5 98.9 --- --- ---

S/E Climb 94.9 95.9 97.7 99.5 99.0 97.6 95.5 93.296.0 97.0 99.0 97.2 95.4 --- --- ---

23.0 V1125 124 124 124 124 125

127 126 126 126 126 --- --- ---Venr Vr 127 127 127 126 126 126 -- --

165 V2 137 137 136 136 135 135 -- --Vref rWY

5000 5100 5320 5600 6020 6740 -- -- 143 5500 5610 5852 6160 6622 --- --- ---

22.0 V1123 122 122 122 122 122125 124 124 124 124 --- --- ---

Venr Vr 125 125 125 125 124 123 -- --165 V2 135 135 135 134 133 133 -- --

Vref rWY4700 4790 4990 5250 5600 6210 -- --

141 5170 5269 5489 5775 6160 --- --- ---

21.0 V1120 120 120 120 120 119 120122 122 122 122 122 --- --- ---

Venr Vr 123 123 123 123 122 121 121 --165.0 V2 134 134 133 133 132 130 130 --Vref rWY

4410 4490 4670 4910 5230 5710 6480 --138 4851 4939 5137 5401 5753 --- --- ---

20.0 V1118 118 118 118 117 117 118120 120 120 120 119 --- --- ---

Venr Vr 122 122 122 121 120 119 118 --165 V2 132 132 132 131 130 128 128 --

Vref rWY4120 4190 4370 4590 4880 5290 5930 --

135 4532 4609 4807 5049 5368 --- --- ---

19.0 V1116 116 116 116 115 115 115118 118 118 118 117 --- --- ---

Venr Vr 120 120 120 119 118 117 116 --165 V2 130 130 130 130 128 127 128 --

Vref rWY3850 3920 4080 4280 4540 4900 5410 --

132 4235 4312 4488 4708 4994 --- --- ---

18.0 V1113 113 113 113 112 112 112 112115 115 115 115 114 --- --- ---

Venr Vr 118 118 118 117 116 115 113 113165 V2 128 128 128 128 126 125 123 122

Vref rWY3560 3630 3770 3950 4190 4510 4930 5580

129 3916 3993 4147 4345 4609 --- --- ---



take

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Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 99.8 100.8 101.5 101.5 101.0 99.6 98.0 96.099.8 100.8 101.5 100.6 98.8 --- --- ---

S/E Climb 95.4 96.2 98.1 100.0 99.0 97.4 95.5 93.298.0 98.6 98.9 97.2 95.4 --- --- ---

23.0 V1129130

129130

129131

130131

131131

132---

--- ---

Venr Vr 130 130 131 131 131 132 -- -- 165 V2 143 143 143 143 143 143 -- --

Vref rWY5440 5530 5880 6370 7040 7980

143 5984 6083 6468 7007 7744 --- --- ---

22.0 V1126 126 126 127 128 129 130128 128 128 128 129 -- -- --

Venr Vr 128 128 128 128 129 129 130 --165 V2 141 141 141 141 141 141 141 --

Vref rWY5060 5150 5420 5860 6470 7290 8560

141 5566 5665 5962 6446 7117 --- --- ---

21.0 V1125 125 124 124 125 126 127127 127 127 125 126 --- --- ---

Venr Vr 127 127 127 125 126 126 127 --165 V2 140 140 140 138 138 138 138 --

Vref rWY4790 4880 5100 5380 5930 6680 7770

138 5269 5368 5610 5918 6523 --- --- ---

20.0 V1124 124 123 122 122 123 124 125126 126 125 124 123 --- --- ---

Venr Vr 126 126 126 124 123 123 124 125165 V2 140 140 139 137 136 136 136 136

Vref rWY4540 4620 4820 5050 5420 6090 7040 8410

135 4994 5082 5302 5555 5962 --- --- ---

19.0 V1122 122 121 121 119 120 121 122124 124 123 123 121 --- --- ---

Venr Vr 125 126 125 123 121 120 121 122165 V2 139 139 138 136 133 133 133 133

Vref rWY4290 4360 4550 4760 5000 5530 6350 7560

132 4719 4796 5005 5236 5500 --- --- ---

18.0 V1120 120 119 119 117 116 118 118122 122 121 121 119 --- --- ---

Venr Vr 124 124 123 122 119 117 118 118165 V2 138 138 137 135 132 129 129 129

Vref rWY4020 4090 4260 4460 4660 4980 5670 6710

129 4422 4499 4686 4906 5126 --- --- ---



take

off

Blee

d ai

r of

f

Flight Planning




T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 99.8 100.8 101.5 101.5 101.0 99.6 98.0 96.099.8 100.8 101.5 100.6 98.8 --- --- ---

S/E Climb 95.4 96.2 98.1 100.0 99.0 97.4 95.5 93.298.0 98.6 98.9 97.2 95.4 --- --- ---

23.0 V1124 124 124 124

126 126 126 126 126 --- --- ---Venr Vr 127 127 126 126 126 -- -- --

165 V2 137 137 136 135 135 -- -- --Vref rWY

5180 5280 5560 5910 6460 143 5698 5808 6116 6501 7106 --- --- ---

22.0 V1122 122 122 122 122 122124 124 124 124 124 --- --- ---

Venr Vr 125 125 125 124 123 123 -- --165 V2 135 135 135 136 134 133 -- --

Vref rWY4871 4960 5210 5540 5970 6680

141 5357 5456 5731 6094 6567 --- --- ---

21.0 V1120 120 120 120 119 120122 122 122 122 121 --- --- ---

Venr Vr 123 124 123 122 121 121 -- --165.0 V2 134 134 133 132 131 130 -- --Vref rWY

4560 4640 4880 5170 5550 6130138 5016 5104 5368 5687 6105 --- --- ---

20.0 V1118 118 118 118 117 117 118120 120 120 120 119 --- --- ---

Venr Vr 122 122 121 121 119 118 118 --165 V2 132 132 132 131 129 128 128 --

Vref rWY4260 4340 4560 4830 5170 5620 6370

135 4686 4774 5016 5313 5687 --- --- ---

19.0 V1116 116 116 115 115 115 115118 118 118 117 117 --- --- ---

Venr Vr 120 120 120 119 118 116 116 --165 V2 130 131 130 129 128 126 125 --

Vref rWY3980 4050 4250 4500 4800 5200 5810

132 4378 4455 4675 4950 5280 --- --- ---

18.0 V1113 113 113 113 112 112 111 113115 115 115 115 114 --- --- ---

Venr Vr 118 118 117 117 115 114 113 113165 V2 128 128 128 127 126 124 122 122

Vref rWY3690 3750 3930 4150 4420 4770 5230 6000

129 4059 4125 4323 4565 4862 --- --- ---



take

off

Blee

d ai

r of

f

Flight Planning


7000 FT Zero Wind or Gradient takeoff


T.O. Gross

Weight X

1,000

Temp °C -25 -20 -10 0 10 20 30 40

T/O power 101.5 101.5 101.5 101.5 101.1 99.8 98.2 96.3101.5 101.5 101.5 100.7 98.9 --- --- ---

S/E Climb 96.7 97.6 99.5 100.1 99.0 97.6 95.5 93.299.2 99.6 99.0 97.1 95.4 --- --- ---

23.0 V1129 129 130 130 131 132 -- --131 131 131 131 132 --- --- ---

Venr Vr 131 131 131 131 132 132 -- -- 165 V2 143 143 143 143 143 143 -- --

Vref rWY 5710 5890 6310 6860 7590 8670 -- -- 143 6281 6479 6941 7546 8349 --- --- ---

22.0 V1126 126 127 128 128 129 -- --128 128 128 128 129 --- --- ---

Venr Vr 128 128 128 128 129 129 -- -- 165 V2 141 141 141 141 141 141 -- --

Vref rWY 5270 5430 5810 6310 6970 7920 -- -- 141 5797 5973 6391 6941 7667 --- --- ---

21.0 V1125 124 124 124 125 127 127 --127 126 125 126 126 --- --- ---

Venr Vr 127 126 125 126 126 127 127 -- 165 V2 140 139 138 138 138 138 138 --

Vref rWY 4980 5100 5340 5790 6390 7210 8460 -- 138 5478 5610 5874 6369 7029 --- --- ---

20.0 V1123 123 122 121 122 123 124 --125 125 124 123 123 --- --- ---

Venr Vr 126 125 124 123 123 124 124 -- 165 V2 139 139 137 136 136 136 136 --

Vref rWY 4720 4820 5040 5300 5830 6560 7650 -- 135 5192 5302 5544 5830 6413 --- --- ---

19.0 V1122 121 121 120 119 120 121124 123 123 122 120 --- --- ---

Venr Vr 125 125 123 122 120 121 121 -- 165 V2 138 138 137 135 133 133 133 --

Vref rWY 4450 4550 4760 4990 5310 5960 6890 -- 132 4895 5005 5236 5489 5841 --- --- ---

18.0 V1120 119 119 118 117 117 118122 121 121 120 118 --- --- ---

Venr Vr 124 123 122 120 118 117 118 -- 165 V2 137 137 135 133 131 129 129 --

Vref rWY 4170 4260 4450 4660 4880 5350 6140 -- 129 4587 4686 4895 5126 5368 --- --- ---



take

off

Blee

d ai

r of

f

Flight Planning


takeoff Zero Wind or Gradient 7000 FT


T.O. Gross

Weight X

1,000

Temp °C

T/O power

S/E Climb

-25 -20 -10 0 10 20 30 40101.5 101.5 101.5 101.5 101.1 99.8 98.2 96.3101.5 101.5 101.5 100.7 98.9 --- --- ---96.7 97.6 99.5 100.1 99.0 97.6 95.5 93.299.2 99.6 99.0 97.1 95.4 --- --- ---

23.0 V1124 124 124 124 124126 126 126 126 126 --- --- ---

Venr Vr 127 126 126 126 126 -- -- -- 165 V2 136 136 136 135 135 -- -- --

Vref rWY 5420 5560 5880 6320 6950 -- -- -- 143 5962 6116 6468 6952 7645 --- --- ---

22.0 V1122 122 122 122 122124 124 123 123 123 --- --- ---

Venr Vr 125 125 123 123 123 -- -- --165 V2 135 135 134 133 133 -- -- --

Vref rWY5090 5210 5510 5870 6410 -- -- --

141 5599 5731 6061 6457 7051 --- --- ---

21.0 V1120 120 120 120 119 120121 121 121 121 120 --- --- ---

Venr Vr 121 121 121 121 120 121 -- --165.0 V2 133 133 132 132 130 130 -- --Vref rWY

4760 4880 5150 5480 5900 6590 -- --138 5236 5368 5665 6028 6490 --- --- ---

20.0 V1118 118 118 118 117 117 118120 120 120 120 119 --- --- ---

Venr Vr 122 121 121 120 119 118 118 --165 V2 132 132 121 120 119 118 118 --

Vref rWY4450 4560 4810 5110 5480 6040 6860 --

135 4895 5016 5291 5621 6028 --- --- ---

19.0 V1116 116 115 115 115 115 115118 118 117 117 117 --- --- ---

Venr Vr 120 120 119 118 117 116 116 --165 V2 130 130 129 128 127 125 125 --

Vref rWY4150 4250 4480 4750 5080 5520 6250 --

132 4565 4675 4928 5225 5588 --- --- ---

18.0 V1113 113 113 113 112 112 112115 115 115 115 114 --- --- ---

Venr Vr 118 117 117 116 115 113 113 --165 V2 128 128 127 126 125 123 122 --

Vref rWY3840 3930 4140 4380 4670 5060 5620 --

129 4224 4323 4554 4818 5137 --- --- --- * For bleed air on increase take-off distance by 100 ft.


take

off

Blee

d ai

r of

f

Flight Planning


climB - maX rate 16,000 TOGW

time/distance/fUelalt

X1000 FT

isatemp

°C

ISA +10°C isa ISA –10°Ctime

min

dist

nmlBs

time

min

dist

nmlBs

time

min

dist

nmlBs

47 - 57 27 156 773 21 118 654 17 93 570

45 - 57 22 124 689 18 124 689 15 98 597

43 - 57 19 105 636 16 84 557 13 69 495

41 - 57 17 91 593 14 73 521 12 60 466

39 - 57 15 79 552 12 64 488 11 53 438

37 - 57 13 68 513 11 56 454 9 47 41035 - 54 12 60 479 10 49 425 9 41 385

33 - 50 10 53 447 9 43 397 8 37 361

31 - 46 9 47 418 8 38 371 7 33 338

29 - 42 9 42 389 7 34 345 6 29 315

27 - 38 8 37 362 7 30 320 6 26 292

25 - 35 7 33 334 6 26 296 5 22 270

23 - 31 6 29 308 5 23 273 5 20 249

21 - 27 6 25 281 5 20 250 4 17 227

19 - 23 5 22 254 4 17 226 4 15 206

1 7 -19 4 19 226 4 15 202 3 13 184

1 5 -15 4 16 199 3 12 178 3 11 162

1 0 - 5 3 9 132 2 7 118 2 6 108

anti-ice sYstems offFOR ℅ N1 SETTING, REFER TO AppROpRIATE ClIMB pOWER CHART

climB speeds – kiaspressUre altitUde - feet

0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000

250 250 250 250 247 235 223 210 195 170 154 153

Wind effect on climB distance (SUBTRACT FOR HEAD WIND, CRUISE ClIMB WEIGHT

ADD FOR TAIl WIND) climBtimemin

WindcrUiseflt VlV

temperatUre

25 kts 50 KTS 100 KTSisa

–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 14113

30 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


18,000 TOGW maX rate - climB


X1000 FT

isatemp

°C


min

dist

nmlBs

time

min

dist

nmlBs

time

min

dist

nmlBs

47 - 57 *75 497 1702 29 166 843 22 121 70045 - 57 28 163 859 22 124 725 18 97 62943 - 57 23 131 768 19 103 662 16 83 50341 - 57 20 111 704 16 88 613 14 72 54439 - 57 17 94 649 14 76 569 12 63 50937 - 57 15 81 599 13 65 528 11 55 47535 - 54 14 70 556 11 57 492 10 48 44433 - 50 12 62 518 10 50 458 9 43 41531 - 46 11 55 482 9 44 427 8 38 38829 - 42 10 49 449 8 39 397 7 34 361

27 - 38 9 43 416 7 34 367 7 30 33425 - 35 8 38 384 7 30 339 6 26 30923 - 31 7 34 353 6 26 312 5 23 28421 - 27 7 29 323 5 23 285 5 20 25919 - 23 6 25 291 5 20 258 4 17 2351 7 -19 5 21 259 4 17 230 4 14 209

1 5 -15 4 18 228 4 14 203 3 12 184

1 0 - 5 3 11 150 3 8 135 2 7 122

5 5 2 5 75 1 4 67 1 3 61

*indicated step climb required. Step climb includes data for time distance & fuel used in the cruise portion based on maximum cruise thrust.



0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000

250 250 250 250 247 235 223 210 195 170 154 153



WindcrUiseflt VlV

temperatUre


–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 1411330 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


climB - maX rate 20,000 TOGW


X1000 FT

isatemp

°C

ISA +10°C isa ISA–10°Ctimemin

distnm

lBstimemin

distnm

lBstimemin

distnm

lBs

47 - 57 *183 1236 3707 *110 739 2436 *42 250 1123

45 - 57 *52 322 1371 29 167 911 22 155 758

43 - 57 30 171 948 23 129 795 19 100 686

41 - 57 24 136 841 20 107 722 16 85 633

39 - 57 21 113 763 17 90 662 14 74 588

37 - 57 18 95 696 15 77 609 13 64 54535 - 54 16 82 643 13 66 565 11 56 50833 - 50 14 72 596 12 58 524 10 49 47431 - 46 12 63 553 10 51 487 9 43 441

2 9 - 42 11 56 513 9 45 451 8 38 410

27 - 38 10 49 475 8 39 417 7 34 37925 - 35 9 44 438 7 34 385 7 30 349

23 - 31 8 38 402 7 30 353 6 26 321

21 - 27 7 34 367 6 26 323 5 23 293

19 - 23 7 29 331 5 23 292 5 19 26517 -19 6 24 293 5 19 260 4 16 23615 -15 5 20 258 4 16 229 4 14 20810 -5 3 12 170 3 9 152 3 8 138

5 5 2 5 84 2 4 76 1 4 68

* Indicated step climb required. Step climb includes data for time distance & fuel used in the cruise portion based on maximum cruise thrust.



0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000250 250 250 250 247 235 223 210 195 170 154 153



Wind crUiseflt VlV

temperatUre


–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 1411330 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


21,000 TOGW maX rate - climB


X1000 FT

isatemp

°C


min

dist

nmlBs

time

min

dist

nmlBs

time

min

dist

nmlBs

47 - 57 *233 1577 4707 *162 1089 3435 *90 595 2124

45 - 57 *102 663 2372 36 209 1067 26 141 845

43 - 57 35 203 1080 26 146 879 21 111 747

41 - 57 27 153 926 21 118 785 18 93 683

39 - 57 22 124 828 18 98 714 15 80 631

37 - 57 19 103 750 16 83 654 13 68 583

35 - 54 17 89 690 14 72 604 12 60 54233 - 50 15 77 638 12 62 560 11 53 50431 - 46 13 68 591 11 55 519 10 46 469

29 - 42 12 60 547 10 48 480 9 41 435 27 - 38 11 53 506 9 42 444 8 36 402

25 - 35 10 47 466 8 37 408 7 31 371

23 - 31 9 41 427 7 32 375 6 27 340

21 - 27 8 36 390 6 28 342 6 24 310

19 - 23 7 31 351 6 24 310 5 21 280

17 - 19 6 26 311 5 21 275 4 17 25015 -15 5 22 273 4 17 242 4 15 22010 - 5 3 13 180 3 10 61 3 9 1465 5 2 6 89 2 4 80 2 4 72




0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000

250 250 250 250 247 235 223 210 195 170 154 153



Wind crUiseflt VlV

temperatUre


–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 14113

30 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


climB - maX rate 22,000 TOGWtime/distance/fUel

altX

1000 FT

isatemp

°C


min

dist

nmlBs

time

min

dist

nmlBs

time

min

dist

nmlBs

47 - 57 *282 1904 5707 *210 1421 4441 *139 933 3123

45 - 57 *152 994 3380 *78 497 1953 30 169 962

43 - 57 *51 308 1436 30 170 987 23 124 818

41 - 57 31 175 1028 24 131 858 19 102 738

39 - 57 25 137 901 20 107 771 17 86 67737 - 57 21 113 809 17 90 701 14 74 62335 - 54 18 96 740 15 77 646 13 64 578

33 - 50 16 83 682 13 67 597 11 56 537

31 - 46 14 73 630 12 58 552 10 50 49829 - 42 13 64 583 10 51 510 9 44 462

27 - 38 11 56 538 9 45 471 8 38 427

25 - 35 10 50 495 8 39 433 7 33 392

23 - 31 9 44 454 7 34 397 7 29 360

21 - 27 8 38 413 7 30 362 6 25 328

19 - 23 7 33 372 6 26 328 5 22 296

17 -19 6 28 330 5 22 291 5 19 264

15 -15 5 23 290 5 18 256 4 16 232

10 - 5 4 14 191 3 11 170 3 9 154

5 5 2 6 94 2 5 84 2 4 76




0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000

250 250 250 250 247 235 223 210 195 170 154 153



Wind crUiseflt VlV

temperatUre


–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 1411330 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


23,000 TOGW maX rate - climBtime/distance/fUel

altX

1000 FT

isatemp

°C


min

dist

nmlBs

time

min

dist

nmlBs

time

min

dist

nmlBs

47 - 57 *327 2214 6707 *258 1740 5441 *186 1258 4127

45 - 57 *197 1304 4380 *125 815 2952 *52 315 1448

43 - 57 *96 618 2437 36 208 1141 26 141 90341 - 57 36 205 1162 27 148 943 21 112 80039 - 57 27 153 985 22 117 834 18 94 727

37 - 57 23 123 874 18 97 753 15 79 666

35 - 54 19 104 795 16 83 690 14 69 615

33 - 50 17 89 730 14 72 636 12 60 57131 - 46 15 78 672 12 62 587 11 53 529

29 - 42 14 68 621 11 54 542 10 46 489

27 - 38 12 60 572 10 47 499 9 41 452

25 - 35 11 53 526 9 41 458 8 35 145

23 - 31 10 46 481 8 36 420 7 31 380

21 - 27 9 40 438 7 31 383 6 27 347

19 - 23 8 35 394 6 27 346 6 23 31317 - 19 7 29 349 5 23 308 5 20 278

15 - 15 6 24 306 5 19 270 4 16 245

10 - 5 4 14 202 3 11 179 3 10 1625 5 2 6 100 2 5 89 2 4 80

*Indicated step climb required. Step climb includes data for time distance & fuel used in the cruise portion based on maximum cruise thrust.



0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 51000

250 250 250 250 247 235 223 210 195 170 154 153



Wind crUiseflt VlV

temperatUre


–10°isa0°

isa+10

5 2 4 8 39 – – – – – – – – – – – –

10 4 8 13 41 – – – – – – – – 20793

15 6 12 25 43 21455 20254 18832

20 8 13 33 45 19033 17720 16453

25 10 20 41 47 16721 15377 14113

30 12 25 50 49 14905 13419 12074


clim

B

Flight Planning


crUise Vmo speeds

m/kias/ktas/n1/ffias anti - ice off

altX

1000

macHn1% RpM AND FUlE FlOW (lBS/HR)

GW 23 22 20 18 16kias

33 0.79 ktas 99.2 98.7 97.9 97.2 96.6285 460 1908 1833 1838 1796 1760

31 0.77 97.4 97.1 96.4 95.8 95.3289 451 1923 1900 1859 1821 1788

29 0.75 96.2 95.9 95.3 94.8 94.3293 443 1961 1938 1899 1865 1833

27 0.73 95.2 94.9 94.4 93.9 93.5297 435 2007 1987 1950 1915 1884

25 0.71 94.3 94 93.6 93.1 92.8301 427 2055 2035 1999 1968 1939

23 0.69 93.4 93.2 92.8 92.4 92305 419 2104 2086 2052 2023 1996

21 0.67 92.7 92.5 92.1 91.7 91.4309 412 2158 2142 2109 2081 2056

19 0.66 92 91.8 91.4 91.1 90.8314 405 2219 2205 2173 2146 2122

17 0.64 91.2 91.1 90.7 90.4 90.1318 397 2287 2272 2242 2217 2195

15 0.62 90.5 90.3 90 89.7 89.5322 391 2357 2344 2317 2292 2271

10 0.59 88.9 88.7 88.5 88.2 88332 375 2552 2539 2514 2490 2469

5 0.45 78.5 78.2 77.8 77.3 76.9274 290 1977 1959 1926 1898 1870


crUi

se

Flight Planning


CRUISE Fl 350 n1, FF, KTAS

GW n1 TEMp °C RAT °CfUel floW

lBs / Hrkias ktas

22 (1) 100.9 -44 -16 1787 271 464 101.3 -54 -26 1881 281 469(2) 100.6 -64 -37 1838 281 458(1) 98.3 -44 -19 1608 257 442 97.4 -54 -29 1643 264 444(2) 96.6 -64 -40 1599 264 433(1) 96.8 -44 -21 1502 245 424 95.1 -54 -31 1491 249 421(2) 94.3 -64 -42 1447 249 411(1) 95.4 -44 -23 1405 234 407 93.3 -54 -34 1365 234 398(2) 92.3 -64 -45 1324 234 388(1) 93.8 -44 -25 1301 220 384 91.8 -54 -36 1270 221 377( 2) 90.8 -64 -47 1228 221 368

20 (1) 100.8 100.2

-44-54

-15-26

17931829

275281

471469

(2) 99.7 -64 -37 1785 281 458(1) 97.8 -44 -18 1592 260 448

96.3 -54 -29 1591 264 444(2) 95.5 -64 -40 1546 264 433(1) 95.6 -44 -21 1445 245 424

93.5 -54 -32 1402 245 415( 2) 93.1 -64 -42 1393 249 411(1) 93.2 -44 -24 1285 227 395

91.6 -54 -34 1276 230 392(2) 90.6 -64 -45 1237 230 383(1) 91.7 -44 -26 1185 213 373 89.8 -54 -37 1160 214 367(2) 88.7 -64 -47 1127 215 359

18 (1) 100.7 -44 -15 1800 279 476 99.2 -54 -26 1784 281 469(2) 98.7 -64 -37 1739 281 458(1) 96.9 -44 -18 1546 260 448

95.4 -54 -29 1546 264 444(2) 94.5 -64 -40 1500 264 433(1) 94.1 -44 -21 1359 242 418

92.5 -54 -32 1354 245 415( 2) 91.5 -64 -43 1312 245 405(1) 92.1 -44 -24 1230 227 395

90.0 -54 -35 1195 227 386(2) 89.4 -64 -45 1185 230 383(1) 89.7 -44 -27 1091 208 364

87.9 -54 -37 1071 209 358(2) 87.2 -64 -48 1056 213 355

16 (1) 100.5 -44 -14 1797 281 47998.4 -54 -26 1744 281 469

(2) 97.8 -64 -37 1698 281 458(1) 96.1 -44 -18 1504 260 448

93.9 -54 -29 1459 260 438(2) 93.7 -64 -40 1460 264 433(1) 93.2 -44 -21 1314 242 418

91.1 -54 -32 1275 242 409(2) 90.6 -64 -43 1270 245 405(1) 90.5 -44 -25 1151 223 389 88.5 -54 -35 1119 223 380(2) 87.9 -64 -46 1111 227 377(1) 87.8 -44 -28 1007 203 356 86.0 -54 -38 988 204 350(2) 85.5 -64 -48 987 209 350

(1) Maximum Cruise Thrust

(2) Thrust For Maximum Range (Approximate)


crUi

se

Flight Planning


n1, FF, KTAS CRUISE Fl 370GW

n1 TEMp °C RAT °CfUel floW

lBs / Hr19as ktas

22 (1) 101.5 101.5

47-57

-19-28

16531727

257266

459463

(2) 101.5 -67 -39 1782 272 461(1) 99.9 -47 -20 1551 249 446 99.0 -57 -30 1591 256 447(2) 99.3 -67 -41 1598 260 442(1) 98.4 -47 -22 1454 238 428 96.6 -57 -33 1440 241 424(2) 96.4 -67 -43 1433 245 420(1) 97.4 -47 -24 1395 230 416 95.2 -57 -35 1354 230 407(2) 94.9 -67 -45 1343 234 403(1) 96.2 -47 -26 1316 220 399 94.1 -57 -36 1280 220 391(2) 93.3 -67 -47 1250 221 383

20 (1) 101.3 101.5

-47-57

-18-28

16581737

262270

467470

(2) 101.1 -67 -38 1766 275 465(1) 98.5 -47 -20 1490 249 446 97.7 -57 -30 1532 256 447(2) 97.9 -67 -41 1538 260 442(1) 96.9 -47 -22 1392 238 428 95.3 -57 -33 1381 241 424 95.0 -67 -43 1372 245 420(1) 95.0 -47 -25 1274 223 405 93.3 -57 -35 1263 227 401 92.4 -67 -46 1225 227 392(1) 93.7 -47 -27 1195 213 387 91.7 -57 -38 1163 213 379(2) 90.7 -67 -49 1128 213 370

18 (1) 101.1 -47 -17 1662 266 473 101.5 -57 -27 1752 274 476(2) 100.3 -67 -38 1715 275 465(1) 97.3 -47 -20 1438 249 446 96.6 -57 -30 1480 256 447(2) 95.7 -67 -41 1440 256 437(1) 95.2 -47 -23 1303 234 422 94.1 -57 -33 1328 241 424(2) 93.1 -67 -44 1288 241 414(1) 93.2 -47 -26 1186 220 399 91.6 -57 -36 1179 223 396(2) 90.5 -67 -47 1143 223 386(1) 91.4 -47 -28 1083 205 374 89.4 -57 -39 1059 206 367(2) 88.4 -67 -49 1032 207 361

16 (1) 101.0 100.6

-47-57

-17-27

16621709

269275

478476

(2) 99.8 -67 -38 1668 275 465(1) 97.0 -47 -20 1434 252 452 95.6 -57 -30 1436 256 447(2) 94.7 -67 -41 1395 256 437(1) 94.1 -47 -23 1255 234 422 92.5 -57 -34 1250 238 419(2) 91.5 -67 -45 1211 238 409(1) 91.5 -47 -26 1106 216 393 89.4 -57 -37 1076 216 384(2) 88.8 -67 -47 1068 220 381(1) 89.3 -47 -29 993 200 365 87.2 -57 -40 965 199 356(2) 86.6 -67 -50 958 204 355




crUi

se

Flight Planning




lBs / Hrkias ktas

22 (1) 101.5 101.5

47--57

-21-30

14751550

236247

444452

(2) 101.5 -67 -40 1597 253 452(1) 101.2 -47 -21 1454 234 440 100.0 -57 -31 1477 241 441(2) 100.1 -67 -41 1480 244 437(1) 100.4 -47 -22 1398 227 428 98.9 -57 -32 1411 234 430(2) 98.7 -67 -43 1404 237 426(1) 99.9 -47 -23 1371 223 422 98.1 -57 -34 1356 227 419(2) 97.8 -67 -44 1347 230 414(1) 99.5 -47 -24 1348 220 417 97.4 -57 -35 1312 221 409(2) 96.9 -67 -45 1288 222 401

20 (1) 101.5 101.5

-47-57

-19-28

15031567

245253

459462

(2) 101.5 -67 -39 1616 259 460(1) 100.0 -47 -20 1414 237 446 99.1 -57 -30 1449 244 447(2) 99.4 -67 -41 1456 248 442(1) 98.5 -47 -22 1325 227 428 97.3 -57 -32 1341 234 430(2) 96.5 -67 -43 1306 234 420(1) 97.5 -47 -24 1271 220 416 95.8 -57 -34 1259 223 413(2) 95.0 -67 -45 1224 223 403(1) 96.4 -47 -25 1208 211 401 94.3 -57 -36 1176 212 393(2) 93.6 -67 -47 1148 212 385

18 (1) 101.3 -47 -18 1508 250 467 101.5 -57 -28 1582 258 470(2) 101.1 -67 -38 1603 262 465(1) 98.5 -47 -20 1354 237 446 97.7 -57 -30 1392 244 447(2) 97.9 -67 -41 1397 248 442(1) 96.9 -47 -22 1262 227 428

95.2 -57 -33 1253 230 424(2) 94.9 -67 -43 1246 234 420(1) 95.0 -47 -25 1155 213 405 93.3 -57 -35 1147 217 401(2) 92.8 -67 -46 1137 220 398(1) 93.7 -47 -27 1088 203 388 91.7 -57 -38 1064 204 380(2) 90.8 -67 -48 1037 205 373

16 (1) 101.2 -47 -17 1512 254 474 101.4 -57 -27 1590 262 476(2) 100.2 -67 -38 1554 262 465(1) 97.9 -47 -20 1340 241 452 96.5 -57 -30 1341 244 447(2) 95.6 -67 -41 1302 244 437(1) 95.0 -47 -23 1178 223 422 93.9 -57 -33 1202 230 424(2) 92.9 -67 -44 1165 230 414(1) 93.0 -47 -26 1073 210 399 91.4 -57 -36 1068 213 396(2) 90.3 -67 -47 1035 213 386(1) 91.2 -47 -28 982 196 375 89.3 -57 -39 963 197 368(2) 88.3 -67 -49 942 199 362




crUi

se

Flight Planning


n1, FF, KTAS CRUISE Fl 410


lBs / Hrkias ktas

22 (1) 101.5 101.5

-57-67

-32-42

13921407

226231

436434

(2) 101.2 -67 -42 1390 230 431(1) 101.1 -57 -32 1367 223 430 100.7 -67 -43 1359 226 426(2) 100.3 - 6 7 - 4 3 1 3 3 4 2 2 3 4 2 0(1 100.7 -57 -33 1342 220 424(2) 100.1 -67 -44 1322 221 418

20 (1) 101.5 101.5

-47-57

-21-30

13881410

224235

442451

(2) 101.5 -67 -40 1449 241 451(1) 100.9 -47 -22 1299 220 434 100.1 -57 -31 1347 230 441(2) 100.2 -67 -41 1351 233 437(1) 100.5 -47 -22 1274 216 428 99.0 -57 -32 1286 223 430(2) 98.8 -67 -43 1281 226 426

(1) 100.0 -47 -23 1250 213 422 98.2 -57 -34 1237 216 419(2) 97.9 -67 -44 1229 220 414(1) 99.7 -47 -24 1234 211 418 97.6 -57 -34 1203 212 410(2) 97.0 -67 -45 1178 212 402

18 (1) 101.5 -47 -19 1366 234 459 101.5 -57 -28 1426 242 462(2) 101.5 -67 -39 1470 247 461(1) 99.9 -47 -20 1283 226 446 99.0 -57 -30 1316 233 447(2) 99.3 -67 -41 1322 236 442(1) 98.4 -47 -22 1202 216 428 97.2 -57 -32 1218 223 430(2) 96.9 -67 -43 1212 226 426(1) 97.5 -47 -24 1154 210 416 95.7 -57 -34 1144 213 413(2) 94.9 -67 -45 1111 213 403(1) 96.3 -47 -25 1095 201 401 94.4 -57 -36 1077 203 395(2) 93.6 -67 -47 1047 203 386

16 (1) 101.3 -47 -28 1375 239 469 101.5 -57 -27 1440 247 471(2) 101.0 -67 -38 1452 250 465(1) 98.3 -47 -20 1224 226 446 97.5 -57 -30 1258 233 447(2) 97.6 -67 -41 1264 236 442(1) 96.7 -47 -22 1141 216 428 95.0 -57 -33 1134 220 424(2) 94.7 -67 -43 1127 223 420(1) 94.7 -47 -25 1045 203 405 93.1 -57 -35 1038 207 401(2) 92.5 -67 -46 1029 210 398(1) 93.4 -47 -27 981 193 386 91.4 -57 -38 960 194 379(2) 90.5 -67 -48 938 195 372




crUi

se

Flight Planning




lBs / Hrkias ktas

20 (1) 101.5 -57 -32 1265 215 435 101.5 -67 -42 1279 220 433(2) 101.2 -57 -32 1246 213 430(1) 100.8 -67 -43 1240 216 426(2) 100.3 -67 -43 1217 213 420(1) 100.9 -57 -33 1233 211 427(2) 100.2 -67 -44 1211 212 418

19 (1) 101.5 -47 -23 1191 206 427 101.5 -57 -31 1278 221 445(2) 101.5 -67 -41 1295 225 442(1) 100.5 -57 -32 1229 216 436 101.0 -67 -41 1261 222 437(2) 100.0 -57 -32 1205 213 430(1) 99.7 -67 -43 1199 216 426 99.6 -57 -33 1183 210 424(2) 99.2 -67 -43 1176 213 420(1) 99.3 -57 -33 1163 207 419(2) 98.6 -67 -44 1138 207 410

18 (1)101.5 -47 -20 1224 216 446 101.5 -57 -30 1286 225 452(2) 101.5 -67 -40 1319 230 451(1) 101.2 -47 -21 1203 213 440

100.0 -57 -31 1222 219 441(2) 100.1 -67 -41 1225 222 437(1) 100.8 -47 -22 1179 210 434 98.9 -57 -32 1167 213 430(2) 98.7 -67 -43 1162 216 426(1) 100.3 -47 -22 1157 206 428 98.1 -57 -34 1122 206 419(2) 97.8 -67 -44 1115 210 414(1) 99.6 -47 -24 1122 201 418 97.5 -57 -34 1094 202 411(2) 96.9 -67 -45 1071 203 403

16 (1) 101.1 -47 -19 1230 223 458 101.5 -57 -28 1302 232 464(2) 101.5 -67 -38 1343 237 462(1) 99.7 -47 -20 1160 216 446 98.8 -57 -30 1190 222 447(2) 99.0 -67 -41 1195 225 442(1) 98.1 -47 -22 1087 206 428 96.9 -57 -32 1102 213 430(2) 96.6 -67 -43 1096 216 426(1) 97.2 -47 -24 1043 200 416 95.4 -57 -34 1035 203 413(2) 94.6 -67 -45 1006 203 403(1) 96.0 -47 -25 990 192 401 94.0 -57 -36 973 194 395(2) 93.2 -67 -47 948 194 386




crUi

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Flight Planning


n1, FF, KTAS CRUISE Fl 450GW

n1 TEMp °C RAT °CfUel floW

lBs / Hrkias ktas

18 (1) 101.5 -57 -32 1153 206 436 101.5 -67 -42 1166 211 435(2) 101. 2 - 6 7 -42 11 5 0 2 0 9 4 3 1(1) 101.0 -57 -32 1131 203 430 100.6 -67 -43 1124 206 426(2) 100.2 -67 -43 1104 203 420(1) 100.8 -57 -33 1118 201 426(2) 100.1 -67 -44 1098 202 418

16 (1) 101.2 -47 -21 1103 205 444 101.5 -57 -29 1173 216 454(2) 101.5 -67 -40 1207 221 453(1) 100.8 -47 -21 1085 203 440 99.6 -57 -31 1104 209 441(2) 100.5 -67 -41 1137 215 442(1) 99.9 -47 -22 1044 197 428 98.6 -57 -32 1055 203 430(2) 98.3 -67 -43 1050 206 426(1) 99.5 -47 -23 1024 194 422 98.2 -57 -33 1034 200 424(2) 97.4 -67 -44 1007 200 414(1) 99.1 -47 -24 1009 192 418 97.1 -57 -34 990 193 411(2) 96.4 -67 -45 965 193 402

14 (1) 100.7 -47 -19 1111 213 459 101.5 -57 -28 1188 222 467(2) 101.5 -67 -38 1226 227 464(1) 99.2 -47 -20 1044 206 446 98.3 -57 -30 1071 212 447(2) 98.6 -67 -41 1075 215 442(1) 97.6 -47 -22 978 197 428 96.4 -57 -32 993 203 430(2) 96.1 -67 -43 987 206 426(1) 96.6 -47 -24 938 191 416 94.9 -57 -34 932 194 413(2) 94.0 -67 -45 906 194 403(1) 95.4 -47 -26 888 183 400 93.2 -57 -36 866 183 391(2) 92.4 -67 -47 846 184 384




crUi

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Flight Planning



G W n1 TEMp °C RAT °CfUel floW

lBs / Hrkias ktas

15 (1) 101.5 -57 -30 1065 203 449

101.5 -67 -40 1081 207 447(2) 100.5 -57 -31 1032 199 441

(1) 101.5 -67 -41 1059 205 442

99.9 -67 -42 1007 199 431

(2) 99.9 -57 -32 1008 197 436

(1) 99.2 -67 -43 984 197 426

99.6 -57 -32 992 194 431

(2) 98.8 -67 -43 967 194 42014 (1) 100.6 -47 -21 986 194 440

101.5 -57 -29 1074 207 457(2) 101.5 -67 -39 1102 212 456

(1) 100.0 -57 -30 1024 202 447

100.9 -67 -40 1056 208 448

(2) 100.1 -47 -22 966 191 434

(1) 99.3 -57 -31 998 199 441

99.4 -67 -41 1000 202 437

(2) 98.3 -57 -32 956 194 430

(1) 98.6 -67 -42 973 199 431

100.0 -47 -22 961 190 432

(2) 97.9 -57 -33 939 191 424

97.5 -67 -43 930 193 419




crUi

se

Flight Planning


time/fUel/distance descentnormal descent1 HiGH speed2 idle poWer3

alt X kias1 0 0 0

time fUel dist kias time fUel dist kias time fUel distmin lBs nm min lBs nm min lBs nm

51 169 16.0 294 100 188 11.7 153 74 171 10.6 79 5449 199 15.6 289 98 197 11.3 147 71 179 10.4 77 5247 214 15.2 283 95 207 10.9 149 68 188 10.1 75 5145 224 14.8 277 91 217 10.5 135 65 197 9.8 73 4943 235 14.3 270 88 228 10.0 128 62 206 9.5 71 47

41 246 13.9 263 84 240 9.6 122 58 216 9.2 69 4439 258 13.4 255 80 252 9.1 116 55 220 8.9 67 4237 271 12.9 247 76 264 8.7 110 52 220 8.6 64 40

35 284 12.4 240 73 271 8.2 103 48 220 8.2 62 383 297 12.0 233 69 275 7.8 97 45 220 7.8 59 3631 300 11.5 226 66 279 7.3 91 42 220 7.5 57 3329 300 11.1 219 62 283 6.9 85 38 220 7.1 54 3127 300 10.6 211 59 287 6.5 79 35 220 6.7 52 2925 300 10.1 201 55 291 6.0 73 32 220 6.3 49 27

23 300 9.5 190 51 295 5.6 66 29 220 5.8 46 2521 300 8.8 177 46 299 5.1 60 26 220 5.4 43 2219 300 8.1 162 41 303 4.7 53 23 220 5.0 40 20

17 300 7.2 143 36 307 4.2 27 21 220 4.5 36 1815 300 6.2 120 30 311 3.8 40 18 220 4.0 32 1610 300 4.3 82 19 321 2.7 22 11 220 2.8 22 11

5 250 2.4 48 10 231 1.4 11 5 220 1.4 12 5

1. set 91 percent n1 AT 47,000 FT, DECREASING N1 1% pER 1000 FT UNTIl OBTAINING 300 KIAS. HOlD 300 KIAS TO COMplETION OF DESCENT. WHEN ANTI-ICE SYSTEMS ARE ON, DECREASE THE DISTANCE 4% AND INCREASE THE FUEl USED 4%. TIME REMAINS THE SAME.

2. HOlD 800 lBS/HOUR FUEl FlOW UNTIl 4500 FT/MINUTE RATE-OF-DESCENT IS OBTAINED. HOlD 4500 FT/MINUTE RATE-OF-DESCENT TO COMplETION OF DESCENT. WHEN THE ANTI-ICE SYSTEMS ARE ON, INCREASE THE FUEl USED BY 10% TIME AND DISTANCE REMAIN THE SAME.

3. SET IDlE pOWER AND HOlD .075 MACH UNTIl OBTAINING 220 KIAS. HOlD 220 KIAS TO COMplETION OF DESCENT USE OF THIS descent in icinG conditions is not recommended as tHe loW poWer settinGs maY not sUstain enGine anti-ice SYSTEM OpERATION.


desc

ent

Flight Planning


HoldinG kias/ffGross WeiGHt

X 1000pRESSURE AlTITUDE – FEET X 1000

30 25 20 15 10 5 sl2 0 kias 210 210 210 210 210 210 210

ff 1137 1167 1213 1265 1329 1404 148619 kias 205 205 205 205 205 205 205

ff 1084 1115 1161 1212 1277 1350 142818 kias 200 200 200 200 200 200 200

ff 1032 1066 1110 1162 1226 1296 13711 7 kias 195 195 195 195 195 195 195

ff 983 1018 1061 1112 1175 1243 131216 kias 190 190 190 190 190 190 190

ff 936 972 1014 1064 1125 1191 125515 kias 185 185 185 185 185 185 185

ff 909 927 968 1019 1077 1138 120114 kias 180 180 180 180 180 180 180

ff 863 899 924 974 1030 1087 1147

speedBrake retracted Gear and flaps Upanti-ice sYstems off

�Note:� When anti-ice system are ON, increase the fuel flow by 5℅

MINIMUM 180 KIAS IN ICING CONDITIONS EXCEpT FOR AppROACH AND lANDING.

Vfr reserVe / alternate VFR Reserve Fuel

45 minutes cruise at 25,000 ft 1,034 lbs.

Alternate Distance(Nautical Miles)

Cruise Altitude(feet)

Fuel Required*(lbs.)

100 48,000 512

200 39,000 868

Approach Fuel - 160 lbs. for 10 minutes.

* - Fuel for climb from sea level using the 250 KIAS/0.67 Mach climb profile, Cruise at long range cruise, normal descent at 16,000 lbs. in zero wind.


desc

ent

Flight Planning


oXYGen sUpplY cHarts

STAN

DARD

OXY

GEN

MASK

AND

49-C

UBIC

FOO

T CY

LIND

ER

AVAI

LABL

E TI

ME IN

MIN

UTES

CA

BIN

ALTI

TUDE

1

COCK

PIT

2 CO

CKPI

T 2

COCK

PIT

2 CAB

IN

2 CO

CKPI

T 4 C

ABIN

2 CO

CKPI

T 6 C

ABIN

2 CO

CKPI

T 8 C

ABIN

2 CO

CKPI

T 10

CAB

IN

2 CO

CKPI

T 12

CAB

IN

2 CO

CKPI

T 13

CAB

IN

8000

10

,000

15,00

0 20

,000

676

713

803

917

338

357

402

459

109

111

115

119

65

66

67

68

46

47

47

48

36

36

37

37

29

29

30

30

25

25

25

25

23

23

23

23

25,00

0 30

,000

35,00

0 37

,000

39,00

0

428

558

755

917

1070

214

279

378

459

535

92

-- -- -- --

58

-- -- -- --

43

-- -- -- --

34

-- -- -- --

28

-- -- -- --

24

-- -- -- --

22

-- -- -- --

OPTI

ONAL

OXY

GEN

MASK

AND

76-C

UBIC

FOO

T CY

LIND

ER

AVAI

LABL

E TI

ME IN

MIN

UTES

CA

BIN

ALTI

TUDE

1

COCK

PIT

2 CO

CKPI

T 2

COCK

PIT

2 CAB

IN

2 CO

CKPI

T 4 C

ABIN

2 CO

CKPI

T 6 C

ABIN

2 CO

CKPI

T 8 C

ABIN

2 CO

CKPI

T 10

CAB

IN

2 CO

CKPI

T 12

CAB

IN

2 CO

CKPI

T 13

CAB

IN

8000

10

,000

15,00

0 20

,000

1040

10

98

1235

14

12

520

549

617

706

167

170

176

183

99

100

102

105

71

71

72

73

55

55

56

56

45

45

45

46

38

38

39

39

35

35

36

36

25,00

0 30

,000

35,00

0 37

,000

39,00

0

659

859

1162

14

12

1647

344

429

581

706

823

141 -- -- -- --

89

-- -- -- --

65

-- -- -- --

52

-- -- -- --

42

-- -- -- --

37

-- -- -- --

34

-- -- -- --

�Note:� • Cockpit masks are assumed to be at the normal setting up to 20,000 ft with a respiratory rate of 10 liters per minute - body temperature satu-rated. Above 20,000 ft, the masks are assumed to be at the 100% setting.

� • passenger oxygen masks are approved for operation at cabin altitude of 25,000 ft and below.

Flight Planning


oXYGen dUration cHartsThe following two graphs provide information for dispatch with less than a full oxygen bottle. (Unless otherwise noted) the following assumptions apply to this figure and are factored into available time calculations:

• Oxygen consumed during a 10 minute emergency descent from Fl510 to 10,000 ft MSl. This defines the starting point of each bottle pressure vs. available time plot.

• After the emergency descent, the cabin altitude for the remainder of the flight is between Fl250 and 10,000 ft MSl.

• All pilot and Copilot oxygen requirements are included. Crew consump-tion rate is 20 lpM (liters/minute) during the emergency descent and 10 lpM thereafter.

• Cockpit masks are at 100% setting regardless of cabin altitude.• Normal pilot usage as required by operating rules when operating above

Fl350 is not taken into account.

oXYGen dUration of 49 cU ft Bottle

SUBTRACT 50 PSI FROM GAUGE READING FOR EVERY 6.7°C (12°F) BOTTLE TEMPERATURE WARMER THAN 21.1°C (70°F)

ADD 50 PSI TO GAUGE READING FOR EVERY 6.7°C (12°F) BOTTLE TEMPERATURE WARMER THAN 21.1°C (70°F)

1800

1700

1600

1500

1400

1300

1200

1100

1000

900

800

700

6000 30 60 90 120

TIME (MINUTES)

Flight Planning


OXYGEN DURATION OF 76 CU FT BOTTlE

SUBTRACT 50 PSI FROM GAUGE READING FOR EVERY 6.7°C (12°F) BOTTLE TEMPERATURE WARMER THAN 21.1°C (70°F)

ADD 50 PSI TO GAUGE READING FOR EVERY 6.7°C (12°F) BOTTLE TEMPERATURE WARMER THAN 21.1°C (70°F)

1800

1700

1600

1500

1400

1300

1200

1100

1000

900

800

700

6000 30 60 90 180

TIME (MINUTES)120 150

Flight Planning


landinG crossWind

fUel WeiGHt conVersionLBS. U.S. gallons

6.75 LBS/GALIMP gallons

8.15 LBS/GALLITERS

1.79 LBS/L25 4 3 1450 7 6 28100 15 12 56200 30 25 112300 44 37 168400 59 49 226500 74 61 279600 89 74 335700 104 86 391800 119 98 447900 133 110 5031000 148 123 5592000 296 245 11173000 444 368 16764000 593 491 22355000 741 614 2973

Citation VII with TFE731-4 Engines land

inG

Flight Planning


landinG Zero Wind or Gradient sea leVel

Anti-Ice Systems ON flaps fUll

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 91.7 92.5 94.3 96.1 97.8 99.6 98.0 96.1

Vapp anti-ice 91.7 92.5 94.3 96.1 97.8 --- --- ---

Vfr se climB 90.5 91.2 92.8 94.7 96.5 97.5 95.6 93.6

VZf anti-ice 90.5 91.4 93.2 95.0 95.4 --- --- ---

23* 138143

land distpart 91 2880 2930 3030 3120 3230 3330 3430 ----

163

178 121/135 4800 4883 5050 5200 5383 5550 5717 ---

20 130135

land distpart 91 2580 2620 2710 2790 2880 2960 3040 3130

155

170 121/135 4300 4367 4517 4650 4800 4933 5067 5217

19 128 land dist

132 part 91 2490 2530 2610 2690 2760 2840 2920 3000

153

168 121/135 4150 4217 4350 4483 4600 4733 4867 5000

18 124 land dist

129 part 91 2380 2420 2490 2570 2640 2710 2790 2860

149

164 121/135 3967 4033 4150 4283 4400 4517 4650 4767

16 118 land dist

122 part 91 2170 2200 2260 2330 2390 2460 2520 2590

143

157 121/135 3617 3667 3767 3833 3983 4100 4200 4317

* - This weight exceeds the maximum designed landing weight. This weight should only be used for emergencies.

Citation VII with TFE731-4 Enginesland

inG

Flight Planning


sea leVel Zero Wind or Gradient landinG

FlApS 20° Anti-Ice Systems ON

Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref G a p W r 91.7 92.5 94.3 96.1 97.8 99.6 98.0 96.1

Va p p anti - ice 91.7 92.5 94.3 96.1 97.8 --- --- ---

V f r s e c l i m B 90.5 91.2 92.8 94.7 96.5 97.5 95.6 93.6

VZf anti - ice 90.5 91.4 93.2 95.0 95.4 --- --- ---

23* 143 land dist

155 part 91 3180 3230 3350 3460 3580 3690 3810 3930

168

183 121/135 5300 5383 5583 5766 5967 6150 6350 6550

20 135146

land distpart 91 2840 2890 2980 3070 3170 3260 3360 3450

160

175 121/135 4733 4817 4967 5117 5283 5433 5600 5750

19 132143

land distpart 91 2730 2780 2860 2950 3040 3130 3220 3310

157

172 121/135 4550 4633 4766 4917 5067 5217 5367 5517

18 129139

land distpart 91 2610 2650 2730 2820 2900 2980 3060 3150

154

169 121/135 4350 4417 4550 4700 4833 4967 5100 5250

16 122 land dist

132 part 91 2370 2410 2480 2550 2620 2690 2770 2840

147

162 121/135 3950 4017 4133 4120 4367 4483 4617 4733



inG

Flight Planning


landinG Zero Wind or Gradient 1,000 FT


Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 92.8 93.7 95.4 97.2 99.0 99.6 98.0 96.1

Vapp anti - ice 92.8 93.7 95.4 97.2 98.7 --- --- ---

Vfr se climB 91.4 92.2 94.0 95.7 97.5 97.5 95.6 93.2

VZf anti - ice 92.0 92.6 94.4 96.0 95.4 --- --- ---

23* 138143

land distpart 91 2970 3020 3120 3230 3330 3440 3550 ---

163

178 121/135 4950 5034 5200 5384 5550 5734 5917 ---

20 130135

land distpart 91 2660 2700 2790 2880 2960 3050 3140 3230

155

170 121/135 4434 4500 4650 4800 4934 5084 5234 5384

19 128132

land distpart 91 2560 2600 2680 2770 2850 2930 3010 3100

153

168 121/135 4267 4334 4467 4617 4750 4884 5017 5167

18 124129

land distpart 91 2450 2490 2570 2640 2720 2800 2870 2950

149

164 121/135 4084 4150 4284 4400 4584 4667 4784 4917

16 118 land dist

122 part 91 2230 2260 2330 2400 2460 2530 2600 2660

143

157 121/135 3717 3767 3884 4000 4100 4217 4334 4434



inG

Flight Planning


1,000 FT Zero Wind or Gradient landinG


Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 92.8 93.7 95.4 97.2 99.0 99.6 98.0 96.1

Vapp anti-ice 92.8 93.7 95.4 97.2 98.7 --- --- ---

Vfr se climB 91.4 92.2 94.0 95.7 97.5 97.5 95.6 93.2

VZf anti-ice 92.0 92.6 94.4 96.0 95.4 --- --- ---

23* 143 land dist

155 part 91 3280 3340 3460 3580 3700 3820 3940 4070

168

183 121/135 5467 5567 5767 5967 6167 6367 6567 6783

20 135 land dist

146 part 91 2930 2970 3070 3170 3270 3370 3470 3570

160

175 121/135 4883 4950 5117 5283 5450 5617 5783 5950

19 132 land dist

143 part 91 2810 2860 2950 3040 3130 3230 3320 3410

157

172 121/135 4683 4767 4917 5067 5217 5383 5533 5683

18 129 land dist

139 part 91 2690 2730 2820 2900 2990 3070 3160 3250

154

169 121/135 4483 4550 4700 4833 4983 5117 5267 5417

16 122 land dist

132 part 91 2440 2480 2550 2620 2700 2770 2850 2920

147

162 121/135 4067 4133 4250 4367 4500 4617 4750 4867



inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

V r e f Ga pWr 93.9 94.8 96.6 98.4 100.1 99.6 98.0 96.1

Vapp anti-ice 93.9 94.8 96.6 98.4 98.7 --- --- ---

V f r se climB 92.4 93.2 95.0 96.8 98.6 --- --- ---

VZf anti-ice 93.3 94.1 95.2 97.7 95.4 --- --- ---

23* 138143 land dist

part 913060 3120 3230 3330 3450 3560 --- ---

163

178 121/135 5100 5200 5383 5550 5750 5933 --- ---

20 130 land dist

135 part 91 2740 2790 2880 2970 3060 3150 3240 3330

155

170 121/135 4567 4650 4800 4950 5100 5250 5400 5550

19 128land dist

part 91132 2640 2680 2770 2850 2940 3020 3110 3190

153

168 121/135 4400 4467 4617 4750 4900 5033 5183 5317

18 124land dist

part 91129 2520 2560 2640 2720 2800 2880 2960 3040

149

164 121/135 4200 4267 4400 4533 4667 4800 4933 5067

16 118land dist

part 91122 2290 2330 2400 2470 2530 2600 2670 2740

143

157 121/135 3817 3883 4000 4117 4217 4333 4450 4567



inG

Flight Planning



FlApS 20° Engine Anti-Ice ON

Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 93.9 94.8 96.6 98.4 100.1 99.6 98.0 96.1

Vapp anti-ice 93.9 94.8 96.6 98.4 98.7 --- --- ---

Vfr se climB 92.4 93.2 95.0 96.8 98.6 --- --- ---

VZf anti-ice 93.3 94.1 95.2 97.7 95.4 --- --- ---

23*143155168

land distpart 91

3390 3450 3580 3700 3830 3960 4090 ---

183 121/135 5650 5750 5967 6167 6383 6600 6817 ---

20135146160

land distpart 91 3020 3070 3170 3270 3370 3480 3580 3690

175 121/135 5033 5117 5283 5450 5317 5800 5967 6150

19132143157

land distpart 91 2900 2950 3040 3140 3230 3330 3430 3520

172 121/135 4833 4917 5067 5233 5383 5050 5717 5867

18129139154

land distpart 91 2770 2810 2900 2990 3080 3170 3260 3350

169 121/135 4617 4683 4833 4983 5133 5283 5433 5583

16

122 land dist

132 part 91 2510 2550 2620 2700 2780 2850 2930 3010

147

162 121/135 4183 4250 4366 4500 4633 4750 4883 5017



inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 95.3 96.2 98.0 99.8 101.0 99.6 98.0 96.1

Vapp anti-ice 95.2 96.2 98.0 99.8 98.7 --- --- ---

Vfr se climB 93.5 94.4 96.1 97.9 99.0 97.6 95.6 93.2

VZf anti-ice 93.9 94.8 96.7 97.2 95.5 --- --- ---

23*138143163

land distpart 91 3160 3220 3330 3450 3560 3680 --- ---

178 121/135 5267 5367 5550 5750 5934 6134 --- ---

20130135155

land distpart 91 2830 2870 2970 3060 3160 3250 3350 ---

170 121/135 4717 4784 4950 5100 5267 5417 5584 ---

19128132153

land distpart 91 2720 2760 2850 2940 3030 3120 3210 3300

168 121/135 4534 4600 4750 4900 5050 5200 5350 5500

18124129149

land distpart 91 2600 2640 2720 2800 2890 2970 3050 3140

164 121/135 4333 4400 4533 4667 4817 4950 5083 5233

16

118 land dist

122 part 91 2360 2390 2470 2540 2610 2680 2750 2830

143

157 121/135 3933 3983 4117 4233 4350 4467 4583 4717



inG

Flight Planning




lH & rH enGine Bleed

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 95.3 96.2 98.0 99.8 101.0 99.6 98.0 96.1

Vapp anti-ice 95.2 96.2 98.0 99.8 98.7 --- --- ---

Vfr se climB 93.5 94.4 96.1 97.9 99.0 97.6 95.6 93.2

VZf anti-ice 93.9 94.8 96.7 97.2 95.5 --- --- ---

23* 143155168

land distpart 91 3510 3570 3700 3830 3970 4100 4240 ---

183 121/135 5850 5950 6167 6383 6617 6833 7067 ---

20 135146160

land distpart 91 3110 3160 3270 3380 3490 3590 3700 3810

175 121/135 5183 5267 5450 5633 5817 5933 6167 6350

19 132143157

land distpart 91 2990 3040 3140 3240 3340 3440 3540 3640

172 121/135 4983 5067 5233 5400 5567 5733 5900 6067

18 129139154

land distpart 91 2850 2900 2990 3080 3180 3270 3360 3460

169 121/135 4750 4833 4983 5133 5300 5450 5600 5767

16 122 land dist

132 part 91 2580 2620 2700 2780 2860 2940 3020 3100

147

162 121/135 4300 4367 4500 4633 4767 4900 5033 5167



inG

Flight Planning


landinG Zero Wind or Gradient pA 4,000 FT


Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 96.6 97.5 99.4 101.3 101.0 99.6 98.0 96.1

Vapp anti-ice 96.6 97.5 99.4 100.5 98.7 --- --- ---

Vfr se climB 94.8 95.7 97.5 99.3 99.2 97.7 95.8 93.4

VZf anti-ice 95.3 96.3 98.2 97.3 95.6 --- --- ---

23* 138143163

land distpart 91 3270 3330 3450 3570 3690 3810 --- ---

178 121/135 5450 5550 5750 5950 6150 6350 --- ---

20 130 land dist part 91 2920 2960 3060 3160 3260 3360 3460 ---

135

155

170 121/135 4867 4934 5100 5267 5434 5600 5767 ---

19 128132153

land distpart 91 2800 2850 2940 3030 3130 3220 3310 ---

168 121/135 4667 4750 4900 5050 5217 5367 5517 ---

18 124 land dist

129 part 91 2680 2720 2810 2890 2980 3070 3150 3240

149

164 121/135 4466 4533 4683 4817 4967 5117 5250 5400

16 118 land dist

122 part 91 2430 2460 2540 2610 2690 2760 2840 2910

143

157 121/135 4050 4100 4233 4350 4483 4600 4733 4850



inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

V r e f Ga pWr 96.6 97.5 99.4 101.3 101.0 99.6 98.0 96.1

Va p p anti-ice 96.6 97.5 99.4 100.5 98.7 --- --- ---

V f r se climB 94.8 95.7 97.5 99.3 99.2 97.7 95.8 93.4

VZ f anti-ice 95.3 96.3 98.2 97.3 95.6 ---- --- ---

23* 143155168

land distpart 91 3630 3700 3830 3970 4110 4260 4400 ---

183 121/135 6050 6167 6383 6617 6850 7100 7333 ---

20 135land dist

part 91146 3210 3270 3380 3490 3600 3720 3830 3950

160

175 121/135 5350 5450 5633 5817 6000 6200 6383 6583

19 132 land distpart 91143 3080 3130 3240 3340 3450 3550 3660 3770

157

172 121/135 5133 5217 5400 5567 5750 5917 6100 6283

18 129 land distpart 91139 2940 2990 3080 3180 3280 3380 3470 3570

154

169 121/135 4900 4983 5133 5300 5467 5633 5783 5950

16 122 land dist

132 part 91 2660 2700 2780 2870 2950 3030 3120 3200

147

162 121/135 4433 4500 4633 4783 4917 5050 5200 5333



inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

V r e f Ga pWr 98.2 99.2 101.1 101.5 101.0 99.6 98.0 96.1

Va p p anti-ice 98.2 99.2 101.1 100.5 98.7 --- --- ---

V f r se climB 94.9 95.9 97.7 99.5 99.0 97.6 95.5 93.2

V Z f anti-ice 96.0 97.0 99.0 97.2 95.4 --- --- ---

23* 138143163178

land dist part 91 3380 3450 3570 3700 3830 --- --- ---

121/135 5634 5750 5950 6167 6383 --- --- ---

20 130135155

land dist part 91 3010 3060 3160 3270 3370 3480 3580 ---

170 121/135 5017 5100 5267 5450 5617 5800 5967 ---

19 128132153

land dist part 91 2890 2940 3030 3130 3230 3330 3420 ---

168 121/135 4817 4900 5050 5217 5383 5550 5700 ---

18 124 land distpart 91129 2760 2800 2890 2980 3070 3160 3260 ---

149

164 121/135 4600 4667 4816 4967 5117 5267 5433 ---

16 118 land distpart 91122 2500 2540 2620 2690 2770 2850 2930 3010

143

157 121/135 4167 4234 4367 4484 4617 4750 4884 5017



land

inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +4098.2 99.2 101.1 101.5 101.0 99.6 98.0 96.198.2 99.2 101.1 100.5 98.7 --- --- ---

94.9 95.9 97.7 99.5 99.0 97.6 95.5 93.296.0 97.0 99.0 97.2 95.4 --- --- ---

Vref Ga pWr

Vapp anti-ice

Vfr se climB

VZf anti-ice

23* 143 land distpart 91155 3760 3830 3970 4120 4270 4420 --- ---

168

183 121/135 6267 6383 6617 6867 7117 7367 --- ---

20 135 land distpart 91146 3320 3380 3490 3610 3730 3850 3970 4090

160

175 121/135 5533 5633 5817 6017 6217 6417 6617 6817

19 132 land distpart 91143 3180 3230 3340 3450 3560 3670 3780 3900

157

172 121/135 5300 5383 5567 5750 5933 6117 6300 6500

18 129 land distpart 91139 3030 3080 3180 3280 3380 3490 3590 3690

154

169 121/135 5050 5133 5300 5467 5633 5817 5983 6150

16 122132147162

land distpart 91 2740 2780 2870 2950 3040 3130 3210 3300

121/135 4567 4633 4783 4917 5167 5217 5350 5500 * - This weight exceeds the maximum designed landing weight. This weight

should only be used for emergencies.


land

inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 99.8 100.8 101.5 101.5 101.0 99.6 98.0 96.0

Vapp anti-ice 99.8 100.8 101.5 101.4 98.7 96.8 --- ---

Vfr se climB 95.4 96.2 98.1 100.0 99.0 97.4 95.5 93.2

VZf anti-ice 98.0 98.6 98.9 97.2 95.4 --- --- ---

23* 138143163178

land distpart 91 3500 3570 3700 3830 3970 --- --- ---

121/135 5834 5950 6167 6384 6617 --- --- ---

20 130135155170

land distpart 91 3110 3160 3270 3380 3490 3600 --- ---

121/135 5184 5267 5450 5634 5817 6000 --- ---

19 128132153168

land distpart 91 2980 3030 3130 3230 3340 3440 3540 ---

121/135 4967 5050 5217 5384 5567 5734 5900 ---

18 124 land dist

129 part 91 2850 2890 2990 3080 3170 3270 3360 ---

149

164 121/135 4750 4817 4984 5134 5284 5450 5600 ---

16 118 land dist

122 part 91 2570 2610 2700 2780 2860 2940 3020 3100

143

157 121/135 4284 4350 4500 4634 4767 4900 5034 5167 * - This weight exceeds the maximum designed landing weight. This weight



inG

Flight Planning




Bleed air on

landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 99.8 100.8 101.5 101.5 101.0 99.6 98.0 96.0

Vapp anti-ice 99.8 100.8 101.5 101.4 98.7 96.8 --- ---

Vfr se climB 95.4 96.2 98.1 100.0 99.0 97.4 95.5 93.2

VZf anti-ice 98.0 98.6 98.9 97.2 95.4 --- --- ---

23* 143155168183

land distpart 91 3890 3970 4120 4280 4440 4600 --- ---

121/135 6483 6617 6867 7133 7400 7667 --- ---

20 135146160175

land distpart 91 3430 3490 3610 3730 3860 3980 4110 ---

121/135 5717 5817 6016 6217 6433 6633 6850 ---

19 132143157172

land distpart 91 3280 3340 3450 3570 3680 3800 3920 4040

121/135 5467 5567 5750 5950 6133 6333 6533 6733

18 129139154169

land distpart 91 3130 3180 3280 3390 3500 3600 3710 3820

121/135 5217 5300 5467 5650 5833 6000 6183 6367

16 122 land dist

132 part 91 2820 2870 2960 3050 3140 3230 3320 3410

147

162 121/135 4700 4783 4933 5083 5233 5383 5533 5683



inG

Flight Planning





landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 101.5 101.5 101.5 101.5 101.0 99.6 98.0 96.0

Vapp anti-ice 101.5 101.5 101.5 100.4 98.7 96.8 --- ---

Vfr se climB 96.7 97.6 99.5 100.1 99.0 97.6 95.5 93.2

VZf anti-ice 99.2 99.6 99.0 97.1 95.4 --- --- ---

23* 138143163

land distpart 91 3630 3700 3840 3980 --- --- --- ---

178 121/135 6050 6167 6400 6633 --- --- --- ---

20 130land dist

part 91135 3210 3270 3380 3490 3610 3720 --- ---

155

170 121/135 5350 5450 5633 5817 6017 6200 --- ---

19 128132153

land distpart 91 3080 3130 3240 3340 3450 3560 --- ---

168 121/135 5133 5217 5400 5567 5750 5933 --- ---

18 124129149

land distpart 91 2940 2990 3080 3180 3280 3380 3480 ---

164 121/135 4900 4983 5133 5300 5467 5633 5800 ---

18 118 land distpart 91122 2650 2700 2780 2860 2950 3030 3120 ---

143

157 121/135 4417 4500 4633 4767 4917 5050 5200 --- * - This weight exceeds the maximum designed landing weight. This weight



inG

Flight Planning





landingWeight

X1,000

OAT °C -25 -20 -10 0 +10 +20 +30 +40

Vref Ga pWr 101.5 101.5 101.5 101.5 101.0 99.6 98.0 96.0

Vapp anti-ice 101.5 101.5 101.5 100.4 98.7 96.8 --- ---

Vfr se climB 96.7 97.6 99.5 100.1 99.0 97.6 95.5 93.2

VZf anti-ice 99.2 99.6 99.0 97.1 95.4 --- --- ---

23* 143 land distpart 91155 4040 4120 4280 4450 4620 4790 --- ---

168

183 121/135 6733 6867 7133 7417 7700 7983 --- ---

20 135146160

land distpart 91 3550 3610 3740 3870 4000 4130 4270 ---

175 121/135 5917 6017 6233 6450 6667 6883 7117 ---

19 132143157

land distpart 91 3390 3450 3570 3690 3810 3940 4060 ---

172 121/135 5650 5750 5950 6150 6350 6567 6767 ---

18 129139154

land distpart 91 3230 3280 3390 3500 3620 3730 3840

---

169 121/135 5383 5467 5650 5833 6033 6217 6400 ---

16 122 land dist

132 part 91 2910 2960 3050 3140 3240 3330 3430 ---

147

162 121/135 4850 4933 5083 5233 5400 5550 5717 ---



inG

Flight Planning


This page Intentionally left blank

ENGINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER/ENG TAB Engine Failure/fire During Takeoff Below V1 . . . . . . . . . . . . . . . . . . . . . . . . E-5 Engine Failure/fire During Takeoff Above V1 . . . . . . . . . . . . . . . . . . . . . . . . E-5 Engine Failure During Final Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-6 Engine Fire (Engine Fire Switch Illuminated, Fire Bell Activated) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-6 Engine Fire Detection System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-7 Engine Fire Extinguisher Bottle Pressure Low . . . . . . . . . . . . . . . . . . . . . . E-7 Fuel Firewall Shutoff Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-7 Hydraulic Firewall Shutoff Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-7 Low or Normal Oil Pressure and Left or Right Oil Press Warn Light ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-8 Low Oil Pressure Indication and Left or Right Oil Press Warn Light OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-8 Oil Chip Detect . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-8 Engine Failure/Precautionary Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . E-9 Single Engine Approach/Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-9 Single Engine Go-around . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-10 In-flight Restart – One Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-11 Double Engine Flameout/Restart – Two Engines . . . . . . . . . . . . . . . . . . . . E-13 Maximum Glide – Emergency Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-13 Engine Fuel Computer Manual Mode ON . . . . . . . . . . . . . . . . . . . . . . . . . . E-14 False Engine Start (Ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-15 Engine Starter Does Not Disengage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-15 High Sustained ITT During Ground Engine Shutdown . . . . . . . . . . . . . . . E-15 Thrust Reverser Inadvertent In Flight Deployment . . . . . . . . . . . . . . . . . . E-16 Thrust Reverser Unlock Light ON In Flight . . . . . . . . . . . . . . . . . . . . . . . . E-17 Thrust Reverser Arm Light On In Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . E-17 Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-18 Inadvertent Stall (Stick Shaker Buffet and/or Roll-Off) . . . . . . . . . . . . . . . E-19APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APU TAB APU Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-21 APU Fails to Shut Down With APU Stop Switch (Ready to Load Light Remains Illuminated) . . . . . . . . . . . . . . . . . . . . . . E-21 APU Relay Engaged, Annunciator Remains Illuminated After Start or Before Shutdown With APU Generator OFF . . . . . . . . . . . . . . . . . . . E-21 APU Fail . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-22FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL TAB

�SchematSc:� Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-23 Fuel Boost Pump ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-24 Low Fuel Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-24 Low Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-24 Fuel Filter Bypass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-24 Wing Transfer Valve Open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-25 Fuselage Fuel Tank Low Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-25 Fuselage Tank Fuel Pump 1 or 2 Light ON . . . . . . . . . . . . . . . . . . . . . . . . . E-25 Fuselage Fuel Transfer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-25 Fuselage Tank Fill Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-26ELECTRICAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ELEC TAB

�tiguhc:� CB Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-27�SchematSc:� Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-28

Cockpit or Cabin Fire or Smoke Detect Light ON . . . . . . . . . . . . . . . . . . . E-29 Before Landing EMER BATTERY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-31 System Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-32 Battery Overheat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-34 Open Current Limiter or Circuit Breaker In AFT Electrical Junction Box . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-34 Master Warning Light ON Steady . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-35 Single Generator Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-35 Loss of Both Generators (Master Warning Reset Will Flash) . . . . . . . . . . E-35 Single Inverter Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-37 Inverter Fail 1 Light ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-37 Inverter Fail 2 Light ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-38 Double Inverter Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-38

Emergency/Abnormal Procedures

Citation VII Operating Handbook�ou Tumtntni Pguposhs Only Jgly 12 E-1

FLIGHT CONTROLS SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLT CONT TAB Autopilot Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-41 Uncontrolled Aircraft Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-41 Jammed Roll Control System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-42 Primary Trim Runaway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-43 Primary Trim Fail . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-43 Stabilizer Trim System Jam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-44 Elevator System Jam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-46 Rudder System Jam . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-47 Rudder Bias System OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-48 Rudder Uncommanded Motion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-48 Flaps Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-48 Flaps Overspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-49 Landing with Flaps Up or At 7° Position . . . . . . . . . . . . . . . . . . . . . . . . . . . E-49 Aileron or Elevator Out Of Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-51 Flaps SPDBK/SP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-51 AOA Probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-51 Stall Warning System Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-51 Speed Brake Annunciator Illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-52 Spoilers Up Annunciator Illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-52 Spoiler Holdown Annunciator Illuminated . . . . . . . . . . . . . . . . . . . . . . . . . E-52 Gust Lock Annunciator Illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-52 No Takeoff Annunciator Illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-52 Aileron Boost System OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-53ENVIRONMENTAL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENVIR TAB

�SchematSc:� Pneumatic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-55 Pressurization System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-56 Cabin Decompression . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-56 Emergency Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-57 Autopilot Emergency Descent Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-58 Environmental System Smoke or Odor . . . . . . . . . . . . . . . . . . . . . . . . . . . E-58 Smoke Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-59 Use of Supplemental Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-59 Emergency Pressurization ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-61 Overpressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-61 HP Precooler Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-62 PAC Overheat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-62 PAC Isolation Valve Open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-63 Duct Overheat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-63 PAC High Pressure Valve Open . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-64 Pac High Flow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-64 Cabin or Accessory Door Unlocked . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-64 Cabin Door Pressure Seal Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-65 Baggage Heater Overheat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-65 Noise, Smoke or Lack of Cooling with The Freon Air Conditioning System Installed and A/C Switch ON . . . . . . . . . . . . . . . . . . . . . . . . . . . E-65ANTI-ICE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANTI-ICE TAB Windshield Fault . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-67 Windshield Overheat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-67 Windshield Air On With Windshield Bleed Air Switch In the OFF Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-68 Cockpit Forward or Side Windshield Cracked or Shattered . . . . . . . . . . . E-68 Windshield Defog Fan Failure or Loss of Defog Airflow to Windshield . E-69 Pitot-Static Heater Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-69 Engine Anti-ice Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-69 Wing Anti-ice Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-70 Horizontal Stabilizer Anti-ice Failure or Ice Suspected to be On the Horizontal Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-70LANDING GEAR/HYDRAULIC . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GEAR/HYD TAB

�SchematSc:� Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-73 Landing Gear Will Not Extend . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-74 Hydraulic Wheel Brake Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-74 Anti-skid System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-74 Nose Wheel Steering Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-75


Citation VII Operating Handbook�ou Tumtntni Pguposhs Only Jgly 12E-2

Hydraulic System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-75 Hydraulic Fluid Temperature Low . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-78 Auxiliary Hydraulic Power ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-80 Parking Brake ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-80AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVN TAB EFIS Red Gun Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-81 Symbol Generator Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-81 EADI Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-82 EHSI Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-82 EFIS or Optional MFD Fan Light Illuminates . . . . . . . . . . . . . . . . . . . . . . . E-83 Single Air Data Computer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-83 Dual Air Data Computer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-84 AHRS Basic Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-84 AHRS DC Power Loss . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-84 Single AHRS Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-84 Heading Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-85 Attitude Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-85 Comparison Monitor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-85 Flight Guidance Computer Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-85





Tis age intentionally leet blann .�

ENGINE FAILURE/FIRE DURING TAKEOFF BELOW V1

1 . ABORT• Maintain directional control• Brakes — APPLY MAXIMUM EFFORT• Throttles — IDLE• Spoilers — EXTEND• Thrust Reverser(s) — DEPLOY

– Verify illumination of thrust reverser ARM, UNLOCK, and DEPLOY lights.

– Verify illumination of RUDDER BIAS light.• Thrust Reverser(s) — REVERSE POWER

(use as required if no fire)�Note:� To obtain maximum braking performance from the anti-skid

system, the pilot must apply continuous maximum effort (no modulation) to the brake pedals.The Takeoff Field Lengths assume that the pilot has applied maximum effort to the brakes at the scheduled V1 speed during the aborted takeoff.

ENGINE FAILURE/FIRE DURING TAKEOFF ABOVE V1

1 . Rotate — VR2 . Landing Gear — UP (after positive rate of climb)3 . Climb — V2 until 1,500 ft AGLAT OR ABOVE 1,500 AGL4 . Accelerate — V2 + 20 Kts.5 . Flaps — RETRACT (V2 + 20 Kts. Minimum)6 . Accelerate — VENR .

If engine fire:

1 . Emergency Procedures, ENGINE FIRE (E-5) — ACCOMPLISH

If engine failure:

1 . Abnormal Procedures, ENGINE FAILURE/ PRECAUTIONARY SHUTDOWN (E-9) — ACCOMPLISH

-OR-2 . Abnormal Procedures, IN-FLIGHT RESTART —

ONE ENGINE (E-11) — ACCOMPLISH



ENGINE FAILURE DURING FINAL APPROACH

1 . AP/TRIM/NWS Disengage Switch — PRESS and RELEASE.2 . Power (operating engine) — INCREASE (as required).3 . Flaps — APPROACH SCHEDULE4 . Airspeed — VAPP MINIMUM5 . Aileron and Rudder Trim — AS REQUIRED6 . Autopilot — ON (as desired)WHEN LANDING ASSURED7 . Autopilot and Yaw Damper — OFF8 . Flaps — SET TO LANDING SCHEDULE9 . Airspeed — VREF

ENGINE FIRE (ENGINE FIRE SWITCH ILLUMINATED, FIRE BELL ACTIVATED)

Illuminates if a fire or an overheat (bleed air leak) condition has been detected. Lifting the FIRE switch cover and pushing the light:

• Closes the fuel and hydraulic shutoff valves. • Closes the affected engine’s thrust reverser

isolation valve. • Arms and directs both fire extinguisher

bottles (white BOTTLE ARMED PUSH lights illuminated).

• Trips generator field relay.1 . Throttle (affected engine) — CONFIRM, THEN IDLE

If FIRE light remains on after 15 seconds:

2 . Engine Fire Switch (affected engine) — CONFIRM, LIFT COVER AND PUSH

3 . Either Illuminated BOTTLE ARMED Light — PUSH4 . Ignition — NORMAL5 . Engine Sync — OFF6 . Throttle (affected engine) — CUTOFF7 . Electrical Load — REDUCE (as required)8 . Engine Anti-Ice (affected engine) — CHECK OFF9 . Boost Pump (affected engine) — OFF10 . Land as Soon as Practical; Refer to Abnormal Procedures, SINGLE

ENGINE APPROACH AND LANDING (E-9)

ENGINEFIREPUSH

1

BOTTLE 1 ARMEDPUSH



continued on next age

If fire warning light on after 30 seconds:11 . Remaining Illuminated BOTTLE ARMED Light — PUSH12 . Land as Soon as Practical; Refer to Abnormal Procedures, SINGLE

ENGINE APPROACH AND LANDING (E-9)

If FIRE WARNING light goes out and secondary indications are not present:

11. Land as Soon as Practical

ENGINE FIRE DETECTION SYSTEM FAILURE

Indicates a failure in the engine fire detection system.

1 . If Indication Occurs on Ground — Correct prior to flight.2 . If Indication Occurs in Flight — FIRE DETECT CB (LH circuit

breaker panel) — CHECK IN

ENGINE FIRE EXTINGUISHER BOTTLE PRESSURE LOW

Indicates either engine or APU fire extinguisher bottle is low.

1 . If Indication Occurs on Ground — Correct condition prior to flight.

FUEL FIREWALL SHUTOFF VALVE

ADVISORY — Indicated that the fuel firewall shutoff valve has been closed by either the LH or RH ENG FIRE PUSH Switch.

HYDRAULIC FIREWALL SHUTOFF VALVE

ADVISORY — Indicated that the hydraulic firewall shutoff valve has been closed by either the LH or RH ENG FIRE PUSH Switch.

FIRE DETFAIL

LH RH

2

FIRE EXTBOTTLE

LOW

3

FUEL F/WSHUTOFF

LH RH

4

HYD F/WSHUTOFF

LH RH

5



continued erom revious age

LOW OR NORMAL OIL PRESSURE AND LEFT OR RIGHT OIL PRESS WARN LIGHT ON

OIL PRESSURE WARN Light illuminated: Illumination indicates oil pressure is lower or

higher than required; illumination also triggers master warning system.

Above 38 PSI:

1 . Land as Soon as Practical

Between 25 and 38 PSI:

1 . Throttle (affected engine) — REDUCE POWER2 . Land as Soon as Practical

Below 25 PSI:

3 . Throttle (affected engine) — CUTOFF1. Accomplish ENGINE FAILURE/PRECAUTIONARY

SHUTDOWN Procedure (E-9)

LOW OIL PRESSURE INDICATION AND LEFT OR RIGHT OIL PRESS WARN LIGHT OFF

OIL PRESSURE WARN Light extinguished:Between 25 and 38 PSI:

1 . Throttle (affected engine) — REDUCE POWERBetween 25 PSI:

1 . Throttle (affected engine) — REDUCE POWER2 . Land as Soon as Practical

OIL CHIP DETECT

ADVISORY — Indicates that metal particles have been detected in the oil pump discharge.

1. Affected Engine — SECURE (if practical); Refer to ENGINE FAILURE/ PRECAUTIONARY SHUTDOWN Procedure (below)

OIL PRESSWARN

LH RH

6

OIL CHIPDETECTOR

LH RH

7



ENGINE FAILURE/PRECAUTIONARY SHUTDOWN

1 . Engine Synchronizer — OFF2 . Throttle (affected engine) — CUTOFF3 . Electrical Load — REDUCE (as required)4 . Fuel Transfer — AS REQUIRED5 . Generator (affected engine) — OFF6 . Ignition (affected engine) — NORM7 . Land as Soon as Practical; Refer to SINGLE ENGINE APPROACH

AND LANDING (E-9).�Note:� The following annunciators will normally be illuminated for

the affected engine after shutdown:• OIL PRESS WARN• FUEL LOW PRESS• GEN OFF• HYD PRESS LOW• STAB ANTI-ICE (if selected ON)• W/S FAULT

SINGLE ENGINE APPROACH/LANDING

BEFORE LANDING:1 . APR ARM/DISARM Switch — PUSH, VERIFY APR ON LIGHT IS

ILLUMINATED2 . Speedbrakes — RETRACT�Note:� Extension of the speedbrakes is not approved during single

engine operation3 . Landing Data — CONFIRM

a. VAPP (per landing flap schedule)b. VREF (per landing flap schedule)c. Fan Speed (N1)

4 . Avionics and Flight Instruments — CHECK / SET5 . Radio Altimeter — SET6 . Fuel Transfer — OFF7 . Engine Synchronizer — OFF8 . Exterior Lights — AS REQUIRED9 . Flaps — APPROACH FLAP SCHEDULE�Note:� Consider flap landing limitations due to inoperative stab

anti-ice if in icing environment.10 . Airspeed — VAPP (MINIMUM)11 . Ignition (operating engine) — ON12 . Passengers — BRIEF13 . Seat Belts / Shoulder Harness — SECURE




14 . Passenger Advisory Lights — PASS SAFE15 . Landing Gear — DOWN AND LOCKED16 . Nosewheel Steering Switch — PUSH, VERIFY ARMED LIGHT IS ON17 . Flaps — SET TO LANDING FLAP SCHEDULE (when landing

assured)18 . Airspeed — VREF (per landing flap schedule)19 . Annunciator Panel — CHECK20 . Autopilot and Yaw Damper — OFFLANDING:1 . Throttle — IDLE2 . Spoilers — EXTEND, AFTER MAIN WHEEL CONTACT3 . Thrust Reverser — DEPLOY AFTER NOSEWHEEL CONTACT

a. Verify illumination of thrust reverser ARM, UNLOCK and DEPLOY lights.

b. Verify illumination of RUDDER BIAS light.4 . Brakes — APPLY (after nosewheel contact)5 . Reverse Power — AS REQUIRED (do not exceed takeoff thrust)�Note:� To avoid possible jamming of the throttle lockout cams, do

not attempt to override the lockout cams.

�Note:� Reverse thrust may need to be reduced during crosswind landings on wet or icy runways.

VREF (GEAR DOWN – 20° FLAPS)WEIGHT 22,000 21,000 20,000 19,000 18,000 17,000 16,000 15,000VAPP 7°

VREF 20° 151* 139*

148* 137*

146135

143132

139129

135125

132122

128118

VREF (GEAR DOWN – FULL FLAPS)WEIGHT 22,000 21,000 20,000 19,000 18,000 17,000 16,000 15,000VAPP 20°

VREF FULL 139* 135*

137* 133*

135130

132128

129125

125121

122118

118114

* Use in an emergency that requires landing at weights in excess of 20,000 lbs.

SINGLE ENGINE GO-AROUND

1 . Thrust — SET FOR TAKEOFF2 . Airplane Pitch Attitude — POSITIVE ROTATION (+10°)�Note:� Flight director go-around mode is recommended to establish

the pitch attitude reference.3 . Speedbrakes — VERIFY RETRACTED4 . Flaps — SET TO APPROACH FLAP SCHEDULE5 . Climb Speed — VAPP MINIMUM (per flap schedule)6 . Landing Gear — UP (when positive climb is established)7 . Flaps up (when clear of obstacle) — VREF + 25 KIAS (per landing

flap schedule)8 . Climb Speed — VENR (165 KIAS)�Note:� Consider Fuel Transfer.




IN-FLIGHT RESTART – ONE ENGINE

Refer to Airstart Envelope (E-12)Following Shutdown — with Starter Assist:

1 . Throttle — CUTOFF2 . Generator — GEN3 . Firewall Shutoff — CHECK OPEN

(HYD F/W SHUTOFF and FUEL F/W SHUTOFF lights extinguished).4 . Fuel Computer — NORM5 . Start Button — PRESS MOMENTARILY6 . Throttle — IDLE AT TURBINE RPM GREATER THAN 10%7 . Engine Instruments — MonitorIf start malfunctions:

8 . Throttle — CUTOFF9 . Starter Disengage Button — PRESS 15 SECONDS AFTER

THROTTLE CUTOFFGo to ENGINE FAILURE/PRECAUTIONARY SHUTDOWN (E-9)

Following Shutdown — Engine Windmilling(15% Turbine RPM (N2) Minimum:

1 . Throttle — OFF2 . Generator — GEN3 . Firewall Shutoff — CHECK OPEN

(HYD F/W SHUTOFF and FUEL F/W SHUTOFF lights extinguished).4 . Ignition — ON5 . Fuel Boost Pump — ON6 . Fuel Computer — NORM7 . Throttle — IDLE AT STABILIZED MINIMUM 15% N2 RPM8 . Engine Instruments — MonitorAfter engine stabilizes:

9 . Boost Pump and Ignition — NORM



AIRSTART ENVELOPE

�Note:� • Starter assist airstarts must be used when stabilized turbine RPM (N2) is below 15 percent.

• Except for Airstart Envelope, the engine start procedure is unchanged with the fuel computer in the manual mode.



DOUBLE ENGINE FLAMEOUT / RESTART – TWO ENGINES

1 . Ignition — BOTH ON2 . Fuel Boost Pump — ON3 . Throttles — IDLE�Note:� Maximum altitude for restart is FL300 (FL200 with MAN FUEL

Computer).

If altitude allows:

4 . Airspeed — INCREASE TO 250 KIAS�Note:� Starter assist airstarts must be used when stabilized turbine

RPM (N2) is below 15%.5 . Fuel Firewall Shutoff — CHECK OPEN6 . Fuel Computers — BOTH NORM7 . All Anti-Ice Switches — OFFIf no start in ten seconds:

8 . Either Start Button — PRESS MOMENTARILY / REPEAT FOR OPPOSITE ENGINE

�CaotN�e:� One start attempt will significantly reduce battery endurance. Two attempts may deplete the batteries.

If no start:

9 . Refer to MAXIMUM GLIDE – EMERGENCY LANDING (below)

MAXIMUM GLIDE – EMERGENCY LANDING

1 . Flaps — UP2 . Airspeed — 150 KIAS3 . Speedbrakes — RETRACT4 . Spoiler Hold Down — ON5 . Landing Gear — UP6 . Transponder — EMERGENCY7 . Air Traffic Control — ADVISE8 . Passenger Advisory Lights — PASS SAFE9 . Crew/Passengers — BRIEF10 . Landing Gear and Flaps — AS REQUIRED for landing anticipated

(Be prepared to use LANDING GEAR DOES NOT EXTEND procedure (E-74).

11 . Auxiliary Hydraulic Power — ON prior to landing�Note:� The anti-skid brakes and the roll spoilers are powered through

the auxiliary hydraulic pump. Lateral control is sufficient for a maximum sideslip of one-half ball without roll spoilers.



ENGINE FUEL COMPUTER MANUAL MODE ON

Steady light indicates that the affected engine fuel computer is operating in the manual mode. Flashing light (on ground before engine start or after shutdown) indicates DEEC has detected a system discrepancy

Indication on ground:

1 . Correct Condition Prior to FlightIndication in flight:

1 . Throttles — ADVANCE to maintain power.�CaotN�e:� Engine acceleration is considerably slower with the fuel

computer operating in the manual mode.

�Note:� There may be a rapid change in engine power when the fuel computer fails to manual mode.

2 . Affected Engine Fuel Computer Switch — MAN3 . Throttle — RETARD�CaotN�e:� Reduce throttle position (affected engine) prior to

attempting computer reset to prevent possible overspeed.4 . Affected Engine Fuel Computer Switch — NORMIf still in MANUAL MODE:

5 . Fuel Computer Switch (affected engine) — MAN

Indicates that the engine synchronization is ON any time the flaps are not in the up position.

1 . Engine Synchronizer — OFF

Illumination indicates engines are configured for reduced idle. Light should illuminate eight seconds after touchdown.

If still in MANUAL MODE:

1 . ADVISORY — Indicates that the engines are in ground idle.

If ground idle light illuminates in flight:

2 . Ground Idle Switch — HIGH3 . Verify Light Extinguished�CaotN�e:� The no takeoff warning system may be active due to a

failure of the landing gear squat switch.

FUEL COMPMANUAL

LH RH

8

ENG SYNC9

GROUNDIDLE

10



FALSE ENGINE START (GROUND)

1 . Throttle — OFFAllow engine to motor for 15 seconds.

2 . Starter Disengage Switch — PRESS MOMENTARILY

ENGINE STARTER DOES NOT DISENGAGE

1 . Starter Disengage Button — PRESSIf starter does not disengage, start relay stuck:

2 . Battery Switch — OFF3 . APU Generator — OFF4 . GPU (if connected) — DISCONNECT5 . Starter Disable Switch (in baggage compartment) — ON6 . Affected Engine — SHUTDOWN

HIGH SUSTAINED ITT DURING GROUND ENGINE SHUTDOWN

1 . Throttle — CHECK OFF2 . Start Button — PRESS MOMENTARILYAfter all indications of fire gone or a minimum of 20% turbine RPM:

3 . Starter Disengage Switch — PRESS4 . Engine Fire Switch (affected engine) — LIFT COVER / PUSH



THRUST REVERSER INADVERTENT IN FLIGHT DEPLOYMENT

Thrust reverser isolation valve is open. System is pressurized.

Thrust reverser is not fully stowed.

Thrust reverser is fully deployed.

1 . Control Wheel / Autopilot — GRIP / DISENGAGE2 . Stow Switch (affected engine) — EMER3 . Throttle (affected engine) — CHECK IDLE4 . Airspeed — REDUCE TO 200 KIAS MAXIMUM

If thrust reverser stows:

5 . UNLOCK and DEPLOY LIGHT — EXTINGUISHED• ARM Light — ILLUMINATED

6 . Throttle (affected engine) — NORMAL OPERATION7 . Airspeed — 250 KIAS MAXIMUM8 . Land as Soon as Practical; Refer to Normal Procedures BEFORE

LANDING

If thrust reverser does not stow:

�Ca�t�ne:� DO NOT ENGAGE AUTOPILOT.

�Note:� • The airplane will pitch up and roll in the direction of the deployed reverser.

• The airplane is controllable through normal use of flight controls.

5 . THRUST REVERSER CIRCUIT BREAKERS (LH PANEL) — CHECK IN

�Note:� The thrust reverser circuit breakers control normal functions on their respective side and emergency stow on the opposite side; i.e., the L/H TR circuit breaker powers normal functions on the L/H thrust reverser and emergency stow on the R/H thrust reverser.

If thrust reverser STILL DOES NOT STOW:

9 . Throttle (affected engine) — CUTOFF10 . Airspeed — 170 KIAS OR BELOW11 . Land As Soon As Possible; Refer to ENGINE FAILURE /

PRECAUTIONARY SHUTDOWN (E-9).

ARM11

UNLOCK12

DEPLOY13



THRUST REVERSER UNLOCK LIGHT ON IN FLIGHT

1 . Stow Switch (affected engine) — EMER2 . Thrust Reverser Levers — CHECK THRUST REVERSER LEVERS

AT STOWED (FULL FORWARD) POSITION3 . Airspeed — MAINTAIN 250 KIAS OR BELOW4 . Land as Soon as Practical — Refer to Normal Procedures, BEFORE

LANDING.

THRUST REVERSER ARM LIGHT ON IN FLIGHT

1 . Thrust Reverser Levers — CHECK THRUST REVERSER LEVERS AT STOWED (FULL FORWARD) POSITION

2 . Stow Switch — VERIFY NORM

If light remains illuminated:

3 . Stow Switch — EMER4 . Land as Soon as Practical — Refer to Normal Procedures, BEFORE

LANDING



DITCHING

Ditching is not approved under FAR 25.801 and was not conducted during certification testing of the airplane. Should ditching be required, the following procedures are recommended:PRELIMINARY1 . Radio — MAYDAY (Identify airplane, position, heading, altitude and

ISA)2 . Transponder — 77003 . Locator Beacon — EMER4 . Environmental Control Unit Package Switches and ENG BLD AIR

Switches — OFF (Prevents water from entering through bleed valves)

5 . Passenger Advisory Switch — PASS SAFE (Check aft facing seats full aft and all seats upright and outboard)

6 . Water Barrier — IN POSITION (IF REQUIRED)�CaotN�e:� The water barrier must be in position prior to opening the

cabin door if this exit is selected as an egress route.7 . Passenger Life Jackets — ON (Life jackets should not be inflated

until outside airplane)APPROACH1 . Gear — UP2 . Flaps — FULL DOWN3 . Speed — VREF4 . Rate-of-Descent — 200 to 300 FT PER MINUTE5 . Plan approach to parallel any uniform swell pattern and attempt to

touch down along a wave crest or just behind it. If the surface wind is very strong or the surface rough and irregular, ditch into the wind on the back side of a wave.

WATER CONTACT1 . Airplane Pitch Attitude — Slightly higher than normal landing

attitude2 . Reduce airspeed and rate-of-descent to a minimum but do not stall

the airplane3 . Throttles — CUTOFF just prior to water contact and contact water

on a crest of a swell, parallel to the major swellAFTER WATER CONTACTUnder reasonable ditching conditions, the airplane should remain afloat an adequate amount of time to launch and board life rafts in an orderly manner.The main cabin door should remain closed and evacuation made through the emergency exit.�Note:� If a water barrier is aboard, it will allow use of the cabin door

as an additional egress route. The water barrier must be in position for ditching if there are more than 9 passengers aboard, and must be installed before the door is opened.



INADVERTENT STALL (STICK SHAKER, BUFFET AND/OR ROLL-OFF)

1 . Autopilot — DISCONNECT2 . Pitch Attitude — REDUCE3 . Roll Attitude — LEVEL4 . Throttles — MAXIMUM THRUST�Note:� NOTE: Pitch attitude should be promptly reduced to at least

0 to 5° nose down. Prompt aileron input may be required to maintain wings level flight.

5 . Airspeed — INCREASE6 . Altitude — RETURN TO PREVIOUS ALTITUDE7 . Throttles — AS REQUIRED



APU FIRE

Illumination indicates APU FIRE detection loops have sensed a fire or an overheat condition.

1 . APU Fire Warning Switch — LIFT COVER/PUSH�CaotN�e:� Procedure may differ according to the type of APU

installation in the aircraft. Refer to the Aircraft Flight Manual .

�Ca�t�ne:� THE BATTERIES MUST BE INSTALLED AND SWITCH IN BATT OR THE GENERATOR(S) MUST BE ON AND OPERATING PRIOR TO AND DURING ALL APU OPERATION TO ENSURE FIRE PROTECTION SYSTEM POWER.

2. APU — VERIFY SHUTDOWN APU RELAY ENGAGE / READY TO LOAD lights extinguished.

3 . APU Bleed Air Valve Switch — CLOSED4 . APU Generator Switch — OFF5 . APU Master Switch — OFF6 . Right Engine Fuel Boost Pump — NORM (If it was turned on for

start)

If APU FIRE annunciator remains illuminated:

7 . LAND AS SOON AS POSSIBLE

APU FAILS TO SHUT DOWN WITH APU STOP SWITCH (READY TO LOAD LIGHT REMAINS ILLUMINATED)

1 . APU MASTER Switch — OFF�Note:� Do not restart APU until condition corrected; indicates

overspeed sensor has failed.

APU RELAY ENGAGED, ANNUNCIATOR REMAINS ILLUMINATED AFTER START OR BEFORE SHUTDOWN WITH APU GENERATOR

OFF

APU relay is closed either for APU start, APU generator operation, or the relay is stuck.

1 . APU Generator — OFF, THEN ON�Note:� The APU RELAY ENGAGED light is illuminated during the first

portion of the start, and should extinguish prior to the READY TO LOAD light illuminating.

2 . APU Ammeter — OBSERVE generator load.3 . APU STRTR DISENGAGE Switch — STRTR DISENGAGE4 . APU Ammeter — VERIFY zero current.

APUFIRE

14

APU RELAYENGAGED

15



IF APU AMMETER CONTINUES TO SHOW CURRENT:

5 . APU Generator — OFF6 . Leave APU Running — Maximum airplane altitude 30,000 ft.7 . Land as soon as practical.8 . After landing:

a. Main Engines — SHUTDOWNb. Starter Disable Switch (Baggage compartment) — ONc. APU Shutdown — VERIFY

An automatic shutdown of the APU has occurred.

Prior to APU start:

ADVISORY: Do not start APU until condition corrected; indicates fire bottle pressure low.

While APU running:

1. APU – VERIFY SHUTDOWN; APU RELAY ENGAGED/READY TO LOAD lights extinguished.

2 . APU Bleed Air Valve Switch — CLOSED3 . APU Generator Switch — OFF4 . APU Master Switch — OFF5 . Right Fuel Boost Pump — NORM Selecting the APU bleed air switch on the

APU panel to OPEN will direct bleed air from the APU to the airplane bleed air system for ECU operation. The BLEED VLV OPEN annunciator will illuminate. Placing the bleed air switch to CLOSE will deactivate the bleed air valve and extinguish the BLEED VAL OPEN annunciator. Check AFM for APU limitations and procedures.

APU FAIL16

BLEED VALOPEN

17



FUEL SCHEMATIC

P

FCU

PP

SECONDARYEJECTORPUMPS

ENGINE-DRIVENFUEL PUMP

6.5 PSID

FCU

6.5 PSID

FUEL LOWPRESS

FUEL HEATER

FUEL FILTER FUEL FILTERBYPASS

FIREWALLSHUTOFFVALVE

TFUS ANKFILL VLV

FUS TANKXFER FAIL

TO APU

PRIMARYEJECTORPUMPS

BOOSTPUMPS

WING FUELTRANSFERVALVE

FORWARD FAIRINGEJECTOR PUMPS

ENGINE FUEL SUPPLY

MOTIVE FLOW

FUSELAGE TANK TRANSFER

FUSELAGEBOOSTPUMPS

FUELSHUTOFFVALVE

F U E L



FUEL BOOST PUMP ON

Indicates that the respective fuel boost pump was either automatically or manually turned ON.

Automatically activated:

1 . Fuel Boost Switch (affected pump) — ON, then NORMCheck for corresponding FUEL LOW PRESS light to illuminate and extinguish as NORM is reselected.

If FUEL BOOST ON light remains illuminated or activates again:

2 . Fuel Boost Switch (affected pump) — ON�Note:� If FUEL BOOST ON light remains illuminated and the FUEL

LOW PRESS light illuminates, fuel pressure from the primary ejector pump may be low.

LOW FUEL PRESSURE

Illumination indicates fuel pressure switch has been actuated by less than 5 PSI fuel pressure.

1 . Fuel Boost — ON (check boost pump circuit breakers in) LH Panel2 . Fuel Quantity — CHECK3 . Fuel Transfer — IF REQUIRED

LOW FUEL QUANTITY

Indicates wing fuel quantity is low. Approximately 350 lbs of usable fuel remains in the indicated tank.

1 . Fuel Boost — ON (check boost pump circuit breakers in)2 . Land as Soon as Practical

FUEL FILTER BYPASS

Indicates fuel filter is contaminated and that there is an actual or impending bypass.

1 . Inspect filter(s) after landing.�Ca�t�ne:� IF BOTH LIGHTS ARE ON, CONSIDER THE POSSIBILITY

OF CONTAMINATED FUEL AND THE PARTIAL OR TOTAL LOSS OF THRUST FROM BOTH ENGINES. LANDING AS SOON AS POSSIBLE MAY BE ADVISED.

FUELBOOST ON

LH RH

18

FUEL LOWPRESS

LH RH

19

FUEL LOWLEVEL

LH RH

20

FUEL FLTRBYPASS

LH RH

21



WING TRANSFER VALVE OPEN

ADVISORY: Indicates that the wing transfer valve has been opened. Required during fuel transfer.

FUSELAGE FUEL TANK LOW LEVEL

Indicates the fuselage tank fuel quantity is low.

1. When FUS TANK XFER FAIL light illuminates — Fuselage Transfer Switch — OFF

FUSELAGE TANK FUEL PUMP 1 OR 2 LIGHT ON

ADVISORY: Indicates that the respective fuselage fuel tank fuel pump is on.

FUSELAGE FUEL TRANSFER FAILURE

Indicates fuselage fuel transfer system has failed to provide adequate pressure.

1 . Fuselage Fuel Pump CB’s (LH panel) — CHECK CLOSED2 . Fuselage Transfer Switch — OFF for two minutes; then ON

If fuel transfer still inoperative:3 . Manual Override FUS TANK X-FER Handle — PULL (located in aft

vanity)�Note:� Verify fuselage transfer switch is ON and FUS tank fuel pump

1/2 lights illuminated.

If fuel transfer still inoperative:4 . Fuselage Transfer Switch — OFF5 . Land as soon as practical

a . Flight time not to exceed one hour from the time that the transfer pump failed when the zero weight C.G. is aft of FS 327

b. No flight time restriction when the zero weight C.G. is forward of FS 327

�Ca�t�ne:� WHEN THE ZERO FUEL C.G. IS AFT OF FS 327, FAILURE TO TRANSFER THE FUEL FROM THE FUSELAGE FUEL TANK COULD RESULT IN THE AIRPLANE CENTER-OF-GRAVITY EXCEEDING THE APPROVED AFT CENTER-OF-GRAVITY LIMIT.

6. Maximum Operating Speed VMO/MMO — 290 KIAS / 0.83 MACH (INDICATED)

7 . Maximum Operating Altitude — 45,000 FT

WING FUEL XFER OPEN

22

FUS TANKLOW

23

FUS TANKFUEL PUMP

1 2

24

FUS TANKXFER FAIL25



FUSELAGE TANK FILL VALVE

Indicates the fuselage tank fill valve is not fully closed. Fuel may transfer from the left wing to the fuselage tank.


1 . Correct condition prior to flight

Indication in flight – (fuselage fuel quantity increasing):

1 . Fuselage Fuel Tank Transfer Switch — ON, then OFF when fuselage fuel quantity reaches zero. Repeat as required.

If LH boost pump OFF:

2. Wing Fuel Transfer — As required to maintain fuel balance (MAX asymmetrical fuel balance is 200 lbs)

3 . Land as soon as practical

If LH boost pump ON:

2 . BATTERY — EMER FOR FIVE MINUTESa. Wing Fuel Transfer — LH FROM RH, as required to balance

fuel.�Note:� The fuselage fuel tank fill valve is closed and the LH boost

pump function associated with the fuselage fuel tank fill valve is disabled with the battery in EMER. The wing fuel quantity is balanced during this period.

3 . BATTERY — BATT FOR FIVE MINUTESa. Wing Fuel Transfer — OFF

�Note:� The battery must be in BATT for five minutes out of every ten minutes to provide sufficient battery charging.

4 . Repeat steps 2 and 3 every ten minutes5 . Land as soon as practical

FUS TANKFILL VLV

26



CB LOCATIONS

R. EMERGENCY BUSRIGHT CB PANEL

AOAAURAL WARNING 2CABIN TEMPDEFOG FANDIGITAL CLOCK 2FLAP AND SPOILER INDICATORFUEL TRANSFERFUSELAGE FUEL QUANTITYHYDRAULIC FLUID VOLUMELH BOOST PUMPLH ENGINE BLEED AIRLH THRUST REVERSER EMERGENCY STOWGEAR WARNING LIGHTSMANUAL CABIN TEMPRH ALTIMETER (VIBRATOR)RH AOARH ENGINE ANTI-ICE

RH FUEL COMPUTERRH FUEL FLOWRH FUEL QUANTITYRH FUEL TEMPRH FUSELAGE PUMPRH HORIZONTAL STABILIZER DE-ICERH IGNITIONRH OIL PRESSURERH OIL TEMPRH PITOT STATICRH THRUST REVERSERRH TURBINE SPEEDRH WING ANTI-ICERATWARNING LIGHT 2WINDSHIELD BLEED AIR

CROSSOVER RIGHT FEED LEFT CB PANEL1

AFT VANITYRH FUEL HEATERRH GENERATOR INLET HEATERRH WING FAIRING ANTI-ICERUDDER BIAS HEAT

RIGHT AUX J. BOX2

A/P 1ADFAPU BLEED AIR VALVEAPU FIRE BOTTLEAPU FIRE DETECTAPU MASTERAPU TESTAUDIO 1AVN ADVISORYCVRDATA STORAGEDME 1FD 1FOOTWELL LIGHTS

HF1LH LANDING LIGHTLH PANEL LIGHTSMAPLIGHTSNAV DATA BASENAV LIGHTSR-NAV 1RAD-TEL/CAB-INPHRADIO ALTIMETER 1RMI 1TRANSPONDER 1VLF 1VOICE ADVISEWING INSPECTION LIGHTS

CROSSOVER LEFT FEED - RIGHT CB PANEL3

EMERGENCY POWER

AUXILIARY HYDRAULIC PUMPBAGGAGE AND TAILCONE LIGHTSBATTERY EMERGENCY DISCONNECTHORIZONTAL STABILIZER PRIMARY TRIMHORIZONTAL STABILIZER PRIMARY TRIMIGNITION (START ONLY)VOLMETERWING TO TANK FILL VALVESTEERING ACCUM BLEED VALVE

BATTERY BUS4

RIGHT FEED- RIGHT CB PANEL RIGHT AUX J-BOX

GROUND RECOGNITION LIGHTSRH BOOST PUNPRH IGNITIONRH RECOGITION LIGHTRH TAXI LIGHTTOILET

RIGHT FEED BUS5

EMERGENCY CROSSOVER

FLAP POWER

CROSSFEED BUS6

LEFT FEED- LEFT CB PANEL LEFT AUX J-BOX

DRAIN HEATERFUSELAGE TANK FILL VALVELH BOOST PUMPLH IGNITION (SECONDARY AND ENG. ANTI-ICE)LH RECOGNITION LIGHTSLH TAXI LIGHTOXYGEN SEAT BELT SIGN

LEFT FEED BUS7

APU COOLING FANLH FUEL HEATERLH GENERATOR INLET HEATERLH WING FAIRING ANTI-ICEREFRESHMENT CENTER

LEFT AUX J-BOX8

AVIONICS EMERG BUS EMERGENCY CROSSOVER

9

LEFT FAN RPMLEFT ITTRIGHT FAN RPMRIGHT ITTSECONDARY PITCH TRIM

EMERGENCYCROSSOVER

LEFT CB PANEL

10

AID DATA COMPUTERCOMM 1HORIZONTAL STABILIZER TRIM ADVISORYNAV 1STANDBY GYRO

11

XOVR RIGHT FEED-LEFT CB PANEL

A/P 2AC INVERTER NO.2ADF 2ANTI-COLLISION LIGHTAUDIO 2CABIN READING LIGHTSCENTER PANELCOMM 2DME 2

RIGHT FEED - RIGHT CB PANEL13

XOVR LEFT FEED-RIGHT CB PANEL

AC INVERTER NO. 1AFT BAGGAGE HEATERAILERON BOOSTANTI-SKIDBATT TEMP AURAL WARN 1COCKPIT TEMPERATUREDIGITAL CLOCK 1ENGINE SYNCEQUIPMENT COOLINGFLAP CONTROLFLIGHT HOUR METERFUSELAGE TANK SHUTOFFGEAR CONTROL

LEFT FEED - LEFT CB PANEL

EMERGENCYAVIONICS BUS

RIGHT CB PANEL EL PANEL LIGHTSENCODING ALTIMETER 2FD 2FLIGHT DATA RECORDERHSI 2NAV 2RH LANDING LIGHTRH PANEL LIGHTRH STARTRADARRMI 2TRANSPONDER 2VLF 2

HYDRAULIC PRESSURELH AOALH ENGINE ANTI-ICE

LH FIRE DETECT

LH FIREWALL SHUTOFF

LH FUEL COMPUTERLH FUEL FLOWLH FUEL QUANTITYLH FUEL TEMPLH FUSELAGE PUMPLH HORIZONTAL STABILIZER DE-ICELH IGNITION (ON POSITION)LH OIL PRESSURELH OIL TEMP

LH PITOT STATIC

LH STARTLH THRUST REVERSERLH TURBINE SPEEDLH WING ANTI-ICEMACH WARNINGPOWER STEERINGPRESSURIZATIONRH BOOST PUMPRH ENGINE BLEED AIRRH THRUST REVERSER EMERGENCY STOWRAT HEATERRUDDER BIASSPOILER HYDRAULICS (HOLDDOWN)WARNING LIGHTS 1WINDSHIELD ALCOHOL

12

CONTROL

RH FIRE DETECT

RH FIREWALL SHUTOFF

RMU 1AHRS 2RMI 1

COCKPIT FLOOD LIGHTSANTI-ICE

WATER WASTEELT

E L E C



ELECTRICAL SYSTEM

A

XOVR RIGHT FEED

LEFT FEEDLEFT CB PANEL

RIGHT FEED BUSAFT J-BOX

L AUX J-BOX

LEFT FEED BUSAFT J-BOX

RIGHT FEEDRIGHT CB PANEL

CROSSFEED BUSAFT J-BOX

LHGEN

GCURH GEN

RESETOFF

VRH STARTRELAY

LH STARTRELAY

GROUNDPOWER

RELAY

APUPOWERRELAY

BATTERYDISCONNECTRELAY

V

LHPOWERRELAY

V

BATTERY RELAY

BATT

EMER

BATT/OFF

EMER

EMERPOWERRELAY

OFF

RHPOWERRELAY

300A300A

75A 75A 75A75A 75A 75A

35A 35A 35A 35A

80A 80A 80A80A 80A 80A

15A

R AUX J-BOX

LEFT CB PANEL

RIGHT CB PANEL

AFT J-BOX

BATT

A

BATT

1

2

NORM

BATT DISC

GCU

ENGINE STARTDISENGAGELH RH

APU

BATTERY BUS

EMER AVIONICS BUS

LH GEN

RESETOFF

RHGEN

XOVR LEFT FEED

AFTJ-BOX

GENOFF

LH RH STARTDISC

LMT CB

RIGHT EMER BUSEMER XOVR BUS

A

11

9

13

3

2

567

8

4

10

12

1



COCKPIT OR CABIN FIRE OR SMOKE DETECT LIGHT ON

Illumination indicates smoke detected in aircraft.

1 . Oxygen Masks — DON and EMERGENCY2 . Smoke Goggles — DON (as required)3 . Oxygen Microphone Switches — MIC OXY MASK4 . Wheel INPH/MIC Switches — INPH POSITION, as required5 . PASS OXY — ON6 . Cockpit Divider Door — OPEN7 . Wemac Boost Switch — OFF8 . Interior Master Switch — OFF9 . Defog Fan — OFF10 . Electrical Source:

If known:

11 . Isolate Faulty Circuits12 . Proceed to FIRE SUPPRESSION and SMOKE REMOVAL

Procedures, as required (E-27)

If unknown:

11. FLOODLIGHTS — FULL BRIGHT12 . CTL LIGHTS (IF INSTALLED) — FULL COUNTER CLOCKWISE13 . Battery Switch — EMER14 . Generators — OFF15 . Standby Control Head Use if required for Com 1 and Nav 1

frequencies (Primus Radio Installation Only)16 . Windshield Bleed Air Manual Valves — OFF17 . Emergency Descent — AS REQUIRED18 . Cabin Pressurization — MANUAL CONTROL ONLY IS AVAILABLE19 . Refer to BEFORE LANDING EMER BATTERY (E-31)�CaotN�e:� Battery power is required to operate pitch trim; excessive

use of trim will prematurely drain the battery.

�CaotN�e:� The engine fuel computers will be operating in manual mode with the Battery switch in EMER and the generators OFF. Advance throttles to maintain power. Engine acceleration is considerably slower with the fuel computers operating in the manual mode.

For operable and inoperable items, refer to SYSTEM STATUS (E-32).�Ca�t�ne:� WHETHER OR NOT THE SMOKE HAS DISSIPATED, IF

IT CANNOT BE VISIBLY VERIFIED THAT THE FIRE HAS BEEN EXTINGUISHED FOLLOWING FIRE SUPPRESSION AND OR SMOKE REMOVAL PROCEDURES, LAND AS SOON AS POSSIBLE.

SMOKEDETECT

27




If severity warrants:

20 . Initiate Smoke Removal by holding the Cabin Pressure Manual Control UP/DOWN switch to UP and turn the Rate knob to Maximum.

21 . All Electrical Switches — OFF�Note:� Emergency Dump switch is inoperative with the Battery in

EMER and the Generators OFF.

If severity warrants:

22 . Fire Extinguisher — UNSTOW AND REMOVE SAFETY PIN23 . Fire — LOCATE AND EXTINGUISH24 . Cockpit PAC Switch — OFF

Cabin Fire:

�Note:� A portable fire extinguisher is located in the cabin inside a compartment placarded FIRE EXTINGUISHER.

1 . Crewmember — ACCOMPLISH THE FOLLOWING:a. Unplug Oxygen Hose / Microphone Cordb. Proceed to Cabin — WITH MASK and GOGGLESc. Portable Oxygen Bottle — LOCATE / PLUG IN HOSE (verify

flow)d. Fire Extinguisher — UNSTOW and remove safety pine. Fire — LOCATE AND EXTINGUISH




BEFORE LANDING EMER BATTERY

�Note:� Fully charged batteries provide at least 30 minutes of operational time (if using the emergency bus).

1. Primary Trim — USE ONLY WHEN LANDING ASSURED (if using the emergency bus)

2 . Landing Data — CONFIRM• VAPP (per landing flap schedule)• VREF (per landing flap schedule)• Takeoff Thrust Fan Speed (N1)• Landing Distance (per landing flap schedule)

3 . Avionics and Flight Instruments — SET4 . Passengers — BRIEF5 . Seats, Seat Belts, Shoulder Harnesses — SECURE�Note:� • Battery power may be insufficient to extend the flaps

for approach and landing. Refer to the table below for appropriate approach speeds and landing distances.

• If more than 30 minutes has elapsed while on emergency battery, consideration should be given to using the EMERGENCY GEAR EXTENSION, LANDING GEAR DOES NOT EXTEND procedure (E-64), and waiting until landing assured to switch the battery to BATT for flap extension.

• If landing on emergency bus, anti-skid will be inoperative. Multiply the scheduled landing distance by 1.6 Depending on the nature of the failure, if the crew determines it to be safe, the battery switch may be turned on just prior to touchdown to regain anti-skid and thrust reversers.

6 . Battery Switch — BATTAdjusted VREF

WT 23K* 22K* 21K* 20K 19K 18K 17K 16K

VREF 0° 168* 165* 159* 155 151 148 143 139

VREF 7° 155* 152* 147* 143 141 137 132 124

VREF 20° 143* 140* 138* 135 132 129 126 122

VREF FULL 138* 135* 133* 130 128 124 121 118

* Use in an emergency which requires landing at weights in excess of 20,000 lbs.

Landing Weight Below 18,000 Lbs:

a. FLAPS UP — Multiply 20° Flap Distance by 1.5b. FLAPS 7° — Multiply 20° Flap Distance by 1.2

Landing Weight Above 18,000 Lbs:c. FLAPS UP — Multiply 20° Flap Distance by 2.0d. FLAPS 7° — Multiply 20° Flap Distance by 1.5

7 . Landing Gear — DOWN AND LOCKED8 . Flaps — LANDING FLAP SCHEDULE




9 . Speedbrakes — RETRACT10 . Airspeed — VREF (per landing flap schedule)11 . Battery Switch — EMER12 . Battery Switch — BATT — JUST PRIOR TO TOUCHDOWN IF CREW

DETERMINES IT TO BE SAFE13 . Nose Wheel Steering Switch — PUSH; VERIFY ARMED LIGHT IS

ON�CaotN�e:� (If landing on Emergency Bus). With the battery switch

selected to EMER, the Thrust Reversers and the Anti-Skid system will be inoperative. However, the Power Brake system continues to function normally. Excessive brake pedal pressure can cause all wheel brakes to lock resulting in a blow out of all main wheel tires.

SYSTEM STATUS

With the battery switch in emer and the generators OFF, only the following items are operational:

• Fan Speed Indicators (N1)• ITT Indicators• AHRS 2• Primary Pitch Trim• Secondary pitch Trim• Horizontal Trim Advisory (clacker)• Cockpit Flood Lights• Emergency Lighting• Cabin Entrance Lighting• NAV 1• RMI or PN101 (Optional)• COMM 1• Digital Air Data Computer 1• Pilot’s Airspeed Indicator• Pilot’s IVSI• AC Inverter 1• Pilot’s and Copilot’s Audio Amps• Standby Attitude Gyro• Auxiliary Hydraulic Pump• Fire Detect & Extinguishing System• Pilot’s Pitot Static Heaters• RMU 1 (Primus Radio Option)• Standby Radio Control Head (Primus Radio Option)





The following items which warrant specific attention, are not operative with the battery switch in emer and the generators OFF:

• Flaps• Aileron Boost (force increased, authority unchanged)• Cabin Pressurization (Manual Control Only)• Electric Windshield Anti-Ice, Copilot’s Pitot Static Heaters,

AOA probe heat (stall warning is inoperative), Horizontal Stabilizer Anti-Ice, and Wing Root heat are inoperative. Engine, Wing, and Windshield Bleed Air valves open.

• All external lights except those specified above.• Flight guidance systems including EFIS displays, autopilot

and AHRS 1, all instruments, avionics, and annunciators except those specified above.

• Normal landing gear operation• Anti-Skid is inoperative




BATTERY OVERHEAT

1 . Amperage — CHECK2 . Battery Disconnect Switch — POSITION TO OVERHEATED

BATTERY3 . Amperage — NOTE DECREASE�Note:� The BATT O'TEMP light may flash after the overheated battery

has been disconnected. This is considered normal as it takes a period of time for the battery to reach its peak temperature and then start to decrease.

If no amperage decrease (battery does not disconnect):

4 . APU Generator — OFF5 . Battery Switch — OFF6 . Battery Voltage — CHECK, one volt less than generator voltage�Note:� Battery voltage may take from 30 seconds to two minutes to

show less than generator voltage. This verifies the batteries are disconnected.

7 . Secondary Trim — ON, as required8 . Land as Soon as Practical — Use Normal Procedure BEFORE

LANDING

If on the ground with EPU battery charging:

1 . Battery Charge Switch (baggage compartment) — NORMAL

OPEN CURRENT LIMITER OR CIRCUIT BREAKER IN AFT ELECTRICAL JUNCTION BOX

Indicates an open current limiter or circuit breaker in the aft junction box.

1 . If Indication Occurs On Ground — Correct condition prior to flight.2 . If Indication Occurs in Flight, Electrical System — MONITOR�Ca�t�ne:� DO NOT TURN OFF THE GENERATORS BECAUSE

PARTIAL ELECTRICAL SYSTEM FAILURE MAY OCCUR ON THE BUS ASSOCIATED WITH A GENERATOR SWITCH TURNED OFF.

�Note:� The generator voltages may vary from 25 to 33 V with an open current limiter. This is normal and will not harm the electrical system.

BATTO’TEMP

1 2

28

AFTJ-BOX

LMT CB

29



MASTER WARNING LIGHT ON STEADY

ADVISORY — Indicates loss of left or right bus power to the annunciator panel; therefore only one-half of the panel is operative. The illuminated Master Warning is the failed side.

1 . WARN LTS Circuit Breakers — CHECK.2 . 75-AMP Circuit Breakers — CHECK3 . LH CB PNL PWR CBs (RH CB Panel) — CHECK4 . Instruments (Hydraulic, Electrical and Engine) — MONITOR

SINGLE GENERATOR FAILURE

Indicates loss of 28 VDC generator power on the designated side. Loss of both generators triggers the Master Warning Reset.

�Note:� Before attempting a generator reset, check voltage of the operating; if greater than 28.5 V, turn operating generator OFF.

1 . Failed Generator — RESET, then GEN

If unable to reset:

2 . Freon Air Conditioning — OFF3 . Failed Generator — OFF4 . Electrical Load — MONITOR5 . APU Generator (if installed) — AS REQUIRED

LOSS OF BOTH GENERATORS (MASTER WARNING RESET WILL FLASH)

1 . Electrical Load — REDUCE AS REQUIRED2 . Interior Master Switch — OFF3 . Freon Air Conditioning (if installed) — OFF4 . Generator Switches — BOTH RESET, THEN OFF5 . Generator Voltage — CHECK (use voltage select switch) left and

right generator readings.�Note:� Generator(s) may not reset if voltage is greater than 29.5 V.

MASTERWARNING

RESET

30

GENOFF

LH RH

31




If on the ground with EPU battery charging:

6 . Generator (closest to 28.5 V) — GEN�Note:� Monitor generator voltage and current for evidence of

satisfactory operation. DO NOT switch on second generator if first generator came on line unless the first generator malfunctions. GCUs may trip both generators off again. If first generator malfunctions, switch it OFF and switch second generator to GEN.

7 . Generator Switch — OFF (if reset attempt fails or generator malfunctions)

8 . Opposite Generator Switch — RESET, then ON (if first GEN OFF)

One generator on line:9 . Electrical Load — REDUCE AS REQUIRED10 . Descent, Approach, Before Landing, Landing — USE NORMAL

PROCEDURES

If neither generator comes on-line and in-flight APU and dual 40or dual 44 AMP/HR batt equipped:

9. 20,000 FT MAX10 . APU – START/GENERATOR — ON (ONE ATTEMPT WITHIN 30

MINUTES OF DUAL GENERATOR FAILURE)11 . ELECTRICAL LOAD — REDUCE AS REQUIRED12 . ALTITUDE — 30,000 FT MAX WITH APU ON13 . DESCENT, APPROACH, BEFORE LANDING, LANDING — USE

NORMAL PROCEDURES

If neither generator comes on-line and not in-flight APU equipped or APU would not start:

9. FLOODLIGHTS — FULL BRIGHT10 . CTL LIGHTS (IF INSTALLED) — FULL COUNTER CLOCKWISE11 . Battery Switch — EMER12 . Standby Control Head — Use as required for COM 1 and NAV 1

frequencies (Primus Radio Installation Only)13 . Windshield Bleed Air Manual Valves — OFF14 . Land as Soon as Practical15 . Refer to BEFORE LANDING EMER BATTERY (E-31)�CaotN�e:� Battery power is required to operate pitch trim; excessive

use of trim will prematurely drain the battery.�CaotN�e:� The engine fuel computers will be operating in manual

mode with the Battery switch in EMER and the generators OFF. Advance throttles to maintain power. Engine acceleration is considerably slower with fuel computers operating in the manual mode.

For operable and inoperable items, refer to SYSTEM STATUS (E-32)




SINGLE INVERTER FAILURE

Indicates alternating current inverter voltage or frequency is outside allowable limits. Loss of both inverters triggers the master warning system.

1 . Circuit Breakers — CHECK (LH panel AC INV 1, AC INV 1 EMER, RH Panel — AC INV 2)

2 . AC INV 1 Circuit Breaker — DO NOT RESET�Note:� Power automatically transfer to the emergency bus.3 . AC INV 1 EMER Circuit Breaker — ATTEMPT ONE RESET

If circuit breaker reopens:

4 . Land as Soon as Practical using remaining (pilot’s or copilot’s) instruments

If circuit breakers are in or reset and inverter is still failed:

INVERTER FAIL 1 LIGHT ON

4 . AC XOVER SWITCH — 2 TO 1, VERIFY PILOT’S AIR DATA INSTRUMENTS ON AND NO FLAGS IN VIEW

5 . Inverter Fail Light — MONITOR, CONFIRM INV FAIL 2 LIGHT IS NOT ON

�Note:� Illumination of the Inverter FAIL 2 light when AC XOVER has been selected indicates that a short is present in the number 1 AC bus.

6 . AC XOVER Switch — NORM�Note:� If the Inverter FAIL 1 light extinguishes, the inverter has

experienced a temporary fault and the inverter has recovered.

If INVERTER FAIL 1 light remains on:

7. AC XOVER Switch — 2 to 1, VERIFY PILOT’S AIR DATA INSTRUMENTS ON AND NO FLAGS IN VIEW

INVERTERFAIL

1 2

32



INVERTER FAIL 2 LIGHT ON

4. AC XOVER SWITCH — 1 TO 2, VERIFY COPILOT’S AIR DATA INSTRUMENTS ON AND NO FLAGS IN VIEW

5 . INVERTER FAIL LIGHT — MONITOR, CONFIRM INV FAIL 1 LIGHT IS NOT ON

�Note:� Illumination of the Inverter FAIL 1 light when AC XOVER has been selected indicates that a short is present in the number 2 AC bus.

6 . AC XOVER SWITCH — NORM�Note:� If the INVERTER FAIL 2 light extinguishes, the inverter has

experienced a temporary fault and the inverter has recovered.

If INVERTER FAIL 2 light remains on:

7. AC XOVER SWITCH — 1 TO 2, VERIFY PILOT’S AIR DATA INSTRUMENTS ON AND NO FLAGS IN VIEW

If respective air data remains inoperative:

8 . AC XOVER Switch — NORM9 . Land as Soon as Practical using remaining (pilot’s or copilot’s)

Instruments

If opposite (second) inverter fails:

8. AC XOVER SWITCH — NORM9 . SECOND INVERTER CIRCUIT BREAKERS — CHECK10 . Refer to DOUBLE INVERTER FAILURE Procedure

DOUBLE INVERTER FAILURE

1 . Airspeed — USE STANDBY INDICATOR (observe placard VMO schedule)

2 . Pilot’s Altimeter — PNEU (copilot’s airspeed and altimeter will be inoperative)

3 . AC INV NO. 1 / AC INV NO. 1 EMER CB’s (LH CB Panel) — PULL

If INVERTER FAIL 2 annunciator extinguishes:

4 . AC XOVER — 2 TO 1�Note:� If inverter 2 recovers, DO NOT RESET the inverter 1 circuit

breaker.5 . Airspeed — USE NORMAL INDICATORS6 . Pilot’s Altimeter — CADC (both pilot’s and copilot’s airspeed and

altimeter will be operative)




If INVERTER FAIL 1 and 2 annunciator remain illuminated:

4. AC INV NO. 1 / AC INV NO. 1 EMER CB’S (LH PANEL) — RESET5 . AC INV NO. 2 CIRCUIT BREAKER (RH CB PANEL) — PULL

If INVERTER FAIL 1 annunciator extinguishes:

7 . AC XOVER — 1 TO 2�Note:� If inverter 1 recovers, DO NOT RESET the inverter 2 circuit

breaker.8 . Airspeed — USE NORMAL INDICATORS9 . Pilot’s Altimeter — CADC (both pilot’s and copilot’s airspeed and

altimeter will be operative)

If INVERTER FAIL 1 and 2 annunciator remain illuminated:

6. Land as Soon as Practical�Note:� � Transponder altitude reporting will be inoperative

� Autopilot will operate only in basic altitude hold

� Pilot’s standby airspeed and pneumatic altitude are the only air data sources




AUTOPILOT FAILURE

1 . AP/TRIM/NWS Disengage Switch — PRESS�Note:� � The SPZ-8000 is a fully monitored autopilot and will

disengage without a significant attitude or heading change.

� Altitude loss was not appreciable during malfunctions during all phases of flight including climb, descent, and coupled approaches.

UNCONTROLLED AIRCRAFT ROLL

1 . AP/TRIM/NWS Disengage Switch — PRESS2 . Control Wheel — STOP ROLL — APPLY OPPOSITE ROLL

CONTROL

If roll not arrested:

3 . Spoiler Hold Down — ON

If roll still not arrested:

4 . Auxiliary Hydraulic Pump — OFF�CaotN�e:� A change in roll and/or yaw during flap selection may

be caused by asymmetric flaps. If an asymmetry occurs during flap selection, return the flap selector to the previous position and land without any further flap position change. If an unexplained asymmetry occurs at a fixed flap selector position, do not attempt any flap position changes prior to landing. These asymmetries may not be annunciated

�CaotN�e:� � Speedbrakes and spoilers are inoperative because the spoiler hold down switch is on. � Limiting crosswind component is 10 Kts when

auxiliary hydraulic pump is off.

� Multiply the landing distance by 1.25.5 . Land as Soon as Practical�Note:� � Roll spoilers are operative with the spoiler hold down

switch ON and the auxiliary hydraulic power switch either in the NORM or ON position.

� Roll spoilers are inoperative with the spoiler hold down switch ON and the auxiliary hydraulic power switch OFF. Lateral control is sufficient for a maximum sideslip of one-half ball without roll spoilers.

F L T



JAMMED ROLL CONTROL SYSTEM

1 . AP/TRIM/NWS Disengage Switch — PRESS2 . Pilot and Copilot Control Wheels — RELEASE3 . Aileron Spoiler Disconnect T-Handle — PULL4 . Pilot’s and Copilot’s Control Wheels — VERIFY ROLL RESPONSE�Ca�t�ne:� PILOT OR COPILOT INPUT FORCE TO THE CONTROL

WHEEL WILL INCREASE THE T-HANDLE PULL FORCE AND MAY PREVENT THE T-HANDLE FROM DISCONNECTING THE PILOT AND COPILOT ROLL CONTROL SYSTEMS.

�Note:� � The pilot’s control wheel will operate the ailerons and the copilot’s control wheel will operate the roll spoilers when the T-handle is pulled.

� The use of rudder pedal input will aid in lateral controllability.

If LEFT pilot’s control wheel response satisfactory:

�CaotN�e:� Inadvertent movement of the copilot’s control wheel could cause a roll spoiler to extend.

5 . Auxiliary Hydraulic Power — OFF6 . Spoiler Hold Down Switch — ON7 . Land as Soon as Practical — Refer to Normal Procedures, Before

Landing.�CaotN�e:� � Multiply the landing distance by 1.25.

� Speed brakes and spoilers are inoperative because the spoiler hold down switch is on.

� Limiting crosswind component is 10 Kts and lateral control is sufficient for a maximum sideslip of one-half ball when the roll spoilers are inoperative.

If LEFT pilot’s control wheel is still jammed:

5. COPILOT’S CONTROL WHEEL — VERIFY ROLL RESPONSE6 . LAND AS SOON AS PRACTICAL — REFER TO NORMAL

PROCEDURES, BEFORE LANDING.�CaotN�e:� • Limiting crosswind component is 10 Kts.

• No aerodynamic force is felt on the copilot’s control wheel when it is moved.

• Rapid control wheel inputs are recommended when only the roll spoilers are operable.



PRIMARY TRIM RUNAWAY

�Ca�t�ne:� IF THE TRIM CONTINUES TO MOVE OR CLICKING CONTINUES TO SOUND AFTER DISENGAGEMENT, THE TRIM SYSTEM HAS RUNAWAY.

1 . AP/TRIM/NWS Disengage Switch — PRESS AND HOLD2 . Secondary Trim Switch — ON (lift guarded cover)3 . Trim — AS REQUIRED (SEC TRIM FAULT light may be illuminated

until the secondary trim is actuated)4 . AP/TRIM/NWS Switch — RELEASE5 . PITCH POWER Circuit Breaker (LH panel) — PULL

If secondary trim functions normally:


If secondary trim also runaway:

6. SECONDARY TRIM SWITCH — OFF7 . SEC PITCH TRIM Circuit Breaker — PULL8 . Land as Soon as PracticalRefer to STABILIZER TRIM SYSTEM JAM Procedure (E-44).

PRIMARY TRIM FAIL

Illumination indicates primary trim control or trim actuator is inoperative; illumination triggers master warning system.

1 . PITCH PWR and PITCH CONTROL CBs — CHECK IN

If trim is still failed:

2 . Secondary Trim Switch — ON (Lift Guarded Cover).3 . Trim — AS REQUIRED (SEC TRIM FAULT Light May Be Illuminated

Until the Secondary Trim is Actuated).4 . Land as Soon as Practical

IF SECONDARY TRIM IS ALSO FAILED, REFER TO STABILIZER TRIM SYSTEM JAM Procedure (E-44).

33 PRI TRIMFAIL

SEC TRIMFAULT

34



STABILIZER TRIM SYSTEM JAM

Stabilizer trim jam at -5.5° to -12°:

1 . Autopilot — OFF2 . Land as Soon as Practical — Refer to Normal Procedures –

BEFORE LANDING

Stabilizer trim jam at -2° to -5.5°:

1 . Autopilot – OFF2 . Land as Soon as Practical with Flaps Up — REFER TO LANDING

WITH FLAPS UP OR AT 7° POSITION (E-49)

Stabilizer trim jam at +2° to -2°:

1 . Autopilot — OFF2 . Land as Soon as Practical�Note:� To reduce control force, maintain the trimmed airspeed as

long as feasible.3 . Spoiler Hold-down — ON4 . Auxiliary Hydraulic Power — ON (Verify AUX-HYD PUMP or AUX-HYD

PRESS light ON).5 . Spoiler Lever — UP�Note:� • The left and right roll control spoilers will be up causing a

nose up trim change.• Lateral control is provided by the ailerons only. Lateral control is sufficient for a maximum sideslip of one-half ball without the roll control spoilers.

• Limiting crosswind component is 10 kts.BEFORE LANDING:1 . Landing Data — CONFIRM

• Airspeed — 165 KIAS MINIMUM• Landing Distance — MULTIPLY 20° FLAP LANDING DISTANCE BY 2.3 DO NOT EXTEND FLAPS FOR LANDING.

• Takeoff Thrust Fan Speed (N1)2 . Avionics and Flight Instruments — CHECK and SET3 . Radio Altimeter — SET4 . Fuel Transfer — OFF (wing and fuselage)5 . Engine Synchronizer — OFF6 . Exterior Lights — AS REQUIRED7 . Flaps — UP8 . Ignition — ON9 . Passengers — BRIEF10 . Seats, Seat Belts and Shoulder Harnesses — SECURE




11 . Passenger Advisory Lights — PASS SAFE12 . Landing Gear — DOWN AND LOCKED13 . Nose Wheel Steering Switch — PUSH; VERIFY ARMED LIGHT IS ON14 . Annunciator Panel — CHECK15 . Yaw Damper — OFF�Ca�t�ne:� � LANDING WITH A TAILWIND OR NEGATIVE GRADIENT

IS PROHIBITED.� DO NOT ATTEMPT TO RESTOW REVERSERS AND

TAKEOFF ONCE THE REVERSERS HAVE STARTED TO DEPLOY. THROTTLE LINKAGE DAMAGE MAY OCCUR.

�Note:� � A power approach to landing is recommended to maintain positive control of sink rate.

� Do not fly steep approach path angle.

Landing:

1 . Flare Attitude — MINIMUM ANGLE2 . Throttles — IDLE3 . Spoiler Hold Down — OFF, after main wheel contact4 . Thrust Reversers — DEPLOY, after nose wheel contact

• Verify illumination of thrust reverser ARM, UNLOCK, and DEPLOY lights.

• Verify illumination of RUDDER BIAS light.5 . Reverse Power — AS REQUIRED (do not exceed 90% N1).6 . Brakes — APPLY after airspeed has decayed to 130 KIAS and nose

wheel ground contact7 . Thrust Reverser Levers — IDLE THRUST at 65 KIAS




ELEVATOR SYSTEM JAM

1 . Autopilot and Yaw Damper — OFF2 . Stabilizer Trim (Primary) — AS REQUIRED for control of pitch

attitude.3 . Land as Soon as Practical with 20° Flaps

Before landing:4 . Landing Data — CONFIRM

• VAPP (per 20° flap schedule)• VREF (per 20° flap schedule)• Landing Distance (per 20° flap schedule)• Takeoff Thrust Fan Speed (N1)

5 . Avionics and Flight Instruments — CHECK AND SET6 . Radio Altimeter — SET7 . Fuel Transfer — OFF (wing and fuselage)8 . Engine Synchronizer — OFF9 . Exterior Lights — AS REQUIRED10 . Flaps — 20°11 . Ignition — ON12 . Passengers — BRIEF13 . Seats, Seat Belts and Shoulder Harnesses — SECURE14 . Passenger Advisory Lights — PASS SAFE15 . Landing Gear — DOWN and LOCKED16 . Nose Wheel Steering Switch — PUSH; VERIFY ARMED LIGHT IS ON17 . Speedbrakes — RETRACT18 . Annunciator Panel — CHECK�Ca�t�ne:� � LANDING WITH A TAILWIND OR NEGATIVE GRADIENT

IS PROHIBITED.

� DO NOT ATTEMPT TO RESTOW REVERSERS AND TAKEOFF ONCE THE REVERSERS HAVE STARTED TO DEPLOY. THROTTLE LINKAGE DAMAGE MAY OCCUR.

�Note:� � A power approach to landing is recommended to maintain positive control of sink rate.

� Do not fly steep approach path angle.

Landing:

1 . Flare Attitude — MINIMUM ANGLE2 . Throttles — IDLE3 . Spoilers and Thrust Reversers — EXTEND AND DEPLOY (after main

wheel contact for speedbrakes/spoilers, after nose wheel contact for thrust reversers)• Verify illumination of thrust reverser ARM, UNLOCK, and

DEPLOY lights.• Verify illumination of RUDDER BIAS light.

4 . Reverse Power — AS REQUIRED (do not exceed 90% N1).5 . Brakes — APPLY



RUDDER SYSTEM JAM

1 . Autopilot and Yaw Damper — OFF2 . Aircraft Control — COMPENSATE WITH AILERON CONTROL/TRIM/

FUEL TRANSFER AS REQUIRED3 . Land as Soon as Practical�Note:� The selection of a wide dry runway is recommended.

Before landing:

1 . Landing Data — CONFIRM• VAPP (per landing flap schedule)• VREF (per landing flap schedule)• Landing Distance (per landing flap schedule)• Takeoff Thrust Fan Speed (N1)

2 . Avionics and Flight Instruments — CHECK AND SET3 . Radio Altimeter — SET4 . Fuel Transfer — OFF (wing and fuselage)5 . Engine Synchronizer — OFF6 . Exterior Lights — AS REQUIRED7 . Flaps — AS REQUIRED8 . Ignition — ON9 . Passengers — BRIEF10 . Seats, Seat Belts and Shoulder Harnesses — SECURE11 . Passenger Advisory Lights — PASS SAFE12 . Landing Gear — DOWN AND LOCKED13 . Nose Wheel Steering Switch — PUSH; VERIFY ARMED LIGHT IS ON14 . Flaps — LANDING FLAP SCHEDULE15 . Speedbrakes — RETRACT16 . Airspeed — VREF (per landing flap schedule)17 . Annunciator Panel — CHECK

Landing:

1 . Throttles — IDLE2 . Spoilers — EXTEND (after main wheel ground contact)3 . Nosewheel Tiller — HOLD TO CENTERED POSITION4 . Nosewheel — LOWER to ground as soon as possible5 . Directional Control — MAINTAIN (with nose wheel steering and

differential braking)



RUDDER BIAS SYSTEM OFF

ADVISORY — Indicates the rudder bias system is OFF.

1 . Rudder Bias Switch — CHECK NORM2 . Rudder Bias Circuit Breaker (left CB panel) — PULL�Note:� With the rudder bias OFF, required rudder panel force may

exceed 240 lbs during single engine operation, at low speeds and high thrust.

RUDDER UNCOMMANDED MOTION

Uncommanded motion during ground operation:

1 . Correct Condition Prior to Flight�Note:� Uncommanded motion can only be detected with both

engines at approximately the same power.

Uncommanded motion during flight:

1 . Rudder Bias Switch — OFF2 . Rudder Bias Circuit Breaker (left CB panel) — RESET, if required.�Note:� With rudder bias off, required rudder pedal force may exceed

240 lbs during single engine operation at low airspeed and high thrust.

FLAPS INOPERATIVE

Indicates a flap system failure; the switchlight includes a reset function.

1 . Flap Handle — POSITION TO ANY DETENT2 . Flap Control Circuit Breaker (left CB panel) — CHECK IN3 . Flap Annunciator/Reset — PUSH4 . Flaps — SET TO REQUIRED DETENT

If flaps still inoperative:5 . Flaps 20° or Full — USE NORMAL LANDING PROCEDURES6 . Flaps UP or 7° — REFER TO LANDING WITH FLAPS UP OR AT 7°

POSITION (E-49)

RUDDERBIAS35

FLAPSINOP

36



FLAPS OVERSPEED

ADVISORY - Flaps are not in the UP position and airspeed is greater than 210 KIAS.

1 . Airspeed — REDUCE2 . Flaps — RETRACT�Note:� Refer to FLAPS INOPERATIVE Procedure if flaps do not

retract.

LANDING WITH FLAPS UP OR AT 7° POSITION

�Ca�t�ne:� � LANDING WITH A TAILWIND OR NEGATIVE RUNWAY GRADIENT IS PROHIBITED (EXCEPT WHEN USING SUPPLEMENT 1 DATA – FLAPS UP ONLY).

� AT WEIGHT ABOVE 18,000 LBS AND BRAKE APPLICATION SPEEDS ABOVE 130 KIAS, BRAKE ENERGY LIMITS MAY BE EXCEEDED. LANDING AT OR BELOW 18,000 LBS IS RECOMMENDED.

� MAXIMUM LANDING FIELD ELEVATION IS 10,000 FT (EXCEPT WHEN USING SUPPLEMENT 1 DATA).

WEIGHT 23 K 22 K 21 K 20 K 19 K 18 K 17 K 16 K 15 K

0° VREF* 168* 165* 162* 158 155 151 147 143 138

7° VREF* 155* 152* 149* 146 143 139 136 132 127

* Maximum Tire Ground Speed is 165 Kts. Consider TAS and WIND.

Before landing:1 . Landing Data — CONFIRM

VREF — Refer to table belowTakeoff Thrust Fan Speed (N1) — COMPUTELanding Distance:

• At or below 18,000 lbs landing weight:• FLAPS UP: Use Supplement 1 Data and Limits (recommended)

or MULTIPLY 20° FLAP DISTANCE BY 1.5• FLAPS 7°: MULTIPLY 20° FLAP DISTANCE BY 1.25

• Above 18,000 lbs landing weight:• FLAPS UP: MULTIPLY 20° FLAP DISTANCE BY 2.0• FLAPS 7°: MULTIPLY 20° FLAP DISTANCE BY 1.5

2 . Avionics and Flight Instruments — CHECK and SET3 . Radio Altimeter — SET4 . Fuel Transfer — OFF (wing and fuselage)5 . Engine Synchronizer — OFF

FLAPSO'SPD

37




6 . Exterior Lights — AS REQUIRED7 . Ignition — ON8 . Passengers — BRIEF9 . Anti-Skid — CHECK ON10 . Seats, Seat Belts, and Shoulder Harnesses — SECURE11 . Passenger Advisory Lights — PASS SAFE12 . Landing Gear — DOWN AND LOCKED13 . Nose Wheel Steering Switch — PUSH; VERIFY ARMED LIGHT IS ON14 . Speedbrakes — RETRACT15 . Airspeed — VREF ADJUSTED16 . Annunciator Panel — CHECK17 . Autopilot and Yaw Damper — DISENGAGED

Landing:

1 . Throttles — IDLE2 . Spoilers and Thrust Reversers — EXTEND AND DEPLOY, AFTER

MAIN WHEEL GROUND CONTACT• Verify illumination of thrust reverser ARM, UNLOCK, and

DEPLOY lights.• Verify illumination of RUDDER BIAS light.

3 . Reverse Power — AS REQUIRED (do not exceed takeoff thrust)4 . Brakes — APPLY, AFTER NOSE WHEEL GROUND CONTACT

• Above 18,000 lbs landing weight, brake application speed is 130 KIAS

�Ca�t�ne:� DO NOT ATTEMPT TO RESTOW THRUST REVERSERS AND TAKEOFF ONCE THE REVERSERS HAVE STARTED TO DEPLOY. THROTTLE LINKAGE DAMAGE MAY OCCUR.

�Note:� To avoid possible jamming of the throttle lockout cam, do not attempt to override the lockout cams.




AILERON OR ELEVATOR OUT OF TRIM

AIL TRIM L or R light ON:

1 . Aileron Trim — TRIM (left or right as indicated until light extinguishes.

ELEV TRIM up or down light ON:

Transient illumination:

ADVISORY — May be normal in some autopilot maneuvers and will extinguish within a few seconds.

Steady illumination:

�CaotN�e:� Grip the control wheel with both hands. A change in trim force will be observed. Do not re-engage the Autopilot.

1 . Stabilizer Trim — RETRIM (autopilot will disengage).

ADVISORY - Fault in the flap/speedbrake and/or spoiler input to the AOA computer. AOA gauge, indexer, and slow/fast are inoperative. Stick shakers are operative in default mode. Stall warning is reduced. On ground, correct prior to flight.

ADVISORY — Indicates a fault in L or R AOA probe/ transmitter. On ground, correct prior to flight.

ADVISORY — indicates the stall warning (stick shaker system is inoperative).

1 . Angle-of-Attack Circuit Breaker (left CB panel) — CHECK (reset if required)

If stall warning light remains on:

2 . Speedbrakes — DO NOT USE IN FLIGHT3 . Maximum Altitude FL450 — DESCEND as required4 . Maintain airspeed at least 165 KIAS. VREF (minimum) may be

maintained on final approach.5 . Limit bank angles to 30 degrees maximum.

AIL TRIM

L R

38

TRI

M

ELEV

UP

DN

39

FLAPSSPDBK/SP40

AOAPROBE

41

42 STALLWARN




ADVISORY — Indicates that the speedbrakes are extended. Normal if selected.

If not selected:

1 . AURAL WARN 1 Circuit Breaker (left CB panel) — CHECK IN ADVISORY — Indicates that the spoilers are

extended. Normal if selected. Prohibited in flight except from emergency descent.

ADVISORY — Indicates that the spoiler hold down system has been turned on manually or automatically.

1 . Maximum Altitude — 45,000 FT�Note:� � Roll control spoilers are operative with the spoiler hold

down switch ON and the auxiliary hydraulic power switch either in NORM or ON position.

� Roll control spoilers are inoperative with the spoiler hold down switch ON and the auxiliary hydraulic power switch OFF. Lateral control is sufficient for a maximum side slip of one-half ball without roll control spoilers.

� The spoiler hold down system, when activated on the ground, is also part of the NO TAKEOFF warning system.

ADVISORY — Indicates that the control surfaces are mechanically locked in neutral position.

1 . Gust Lock Handle — CHECK DISENGAGED (full in)�Note:� The GUST LOCK light ON will activate the NO TAKEOFF

warning system if the gustlock disengagement system has failed.

ADVISORY — Indicates an improper takeoff configuration.

Activation on ground:

1 . Takeoff — ABORT2 . Verify Each of the Following:

• Flaps — SET FOR TAKEOFF SCHEDULE• Speedbrake/Spoiler Lever — FULL FORWARD (confirm

SPOILERS UP light and SPEED BRAKE light are extinguished)• Stabilizer Trim — SET per Primary Trim Takeoff Setting vs.

Airplane Center of Gravity Standard Chart• Spoiler Hold Down Switch — OFF• Gustlock — FULLY STOWED — VERIFY full and unrestricted

travel on all controls• Cabin Door — CLOSED AND LATCHED with CAB DOOR

UNLOCKED annunciator extinguished.

SPEEDBRAKE

43

SPOILERSUP44

SPOILERHOLDOWN

45

GUSTLOCK46

NOTAKEOFF

47





Activation on ground:

1 . Speedbrake Lever — FULL FORWARD�Note:� The no takeoff aural warning horn will activate when the

speedbrakes are extended and the flaps are in any position other than up and the airplane is less than 500 ft above ground level.

AILERON BOOST SYSTEM OFF

1 . Aileron Boost CB (left CB panel) — CHECK IN2 . Aileron Boost System — IN-FLIGHT RE-ENGAGEMENT

• Autopilot — OFF• Aileron Trim — POSITION INDEX TO CENTER REFERENCE• Pilot’s Control Wheel — MAKE POSITIVE ROLL INPUT AND

RELEASE• Aileron Boost Switch — RESET, THEN ON

�Note:� Trim airplane in pitch for level flight.

AIL BOOSTOFF

48




PNEUMATIC SYSTEM

ANTI-ICEEMERGPRESSSOV

HP BLEED AIR

LP BLEED AIR

CONDITIONED AIR

COOL AIR

RAM AIR

T

CK

PTPA

CC

AB

PAC

TOCABIN

P

TO WSHLDANTI-ICE

FROM RAM AIR SCOOP

T

OVERBOARD

P

M

TOWEMAC

OUTLETS

TOCOCKPIT

TOWEMAC

OUTLETS

TO SERVICE AIR

TO WINGANTI-ICE

FROML ENG

TO ENGANTI-ICE

HP BLEED

HP PRECLRO’HEAT

DUCTO’HEAT

EMERGPRESSSOV

ISOLATIONVALVE

ENGINE BLEED VLV

FROMR ENG

PAC BLEED SELECT VLV

PACBLEED

SELECTVLV

HP PRECLRO’HEAT

PRECOOLERHEAT

EXCHANGERTOSERVICEAIR ANDRUDDERBIAS

T T

FROMAPU

COCKPITAIR MIXEDMUFF

COCKPITPRESSUREREGULATINGVALVE(NORMALLYOPEN-LOW)

PRIMARYHEATEXCHANGER

FROM RAM AIR SCOOP

CABINPRESSUREREGULATINGVALVE

ANTI-ICE PNEUMATICVALVE(35°F)

TEMPCONTROLVALVE

CABIN PAC(UPPER)

WATERSEPARATOR

COCKPIT PAC(LOWER)

225°F

475°F

CABINAIRMIXEDMUFF

FROM RIGHTENGINE

T

T225°F

T

475°FT

T T

PACO’HEAT

TO LEFTOVERHEAD

SECONDARYHEAT

EXCHANGER

PACO’HEAT

FROM LEFTENGINE

TO RIGHTOVERHEAD

FROMAPU

PACVLVPAC

VLV

MIXINGMUFF

MIXINGMUFF

DUCTO’HEAT

E N V I R



PRESSURIZATION SYSTEM FAILURE

Indicates cabin altitude greater than 8,500 ft.

If cabin altitude 8,500 light ON, 10,000 ft aural warning not ON:

�Note:� The amber CABIN ALTITUDE 8,500 FT light will illuminate whenever the cabin altitude exceeds approximately 8,500 ft. The following steps should be accomplished until the cause of the pressurization loss is determined.

1 . AUTO/ALTITUDE SELECT Switch — ALTITUDE SELECT2 . Cabin Altitude Selector — REDUCE selected altitude3 . PAC Switches — HIGH, if required to maintain desired cabin

pressure altitude (maximum altitude FL 450).4 . PAC BLD SELECT Switch — HP, if required to maintain cabin pressure.

If cabin altitude stabilizes, continue flight in the configuration that maintains cabin pressurization.

If cabin altitude continues to increase:

5 . MAN/NORM Switch — MAN6 . UP-DOWN Manual Control — DOWN

If cabin altitude stabilizes, continue flight in the configuration that maintains cabin pressurization.

If not arrested by 10,000 ft (aural warning sounds):

7 . ACCOMPLISH CABIN DECOMPRESSION CHECKLIST.

CABIN DECOMPRESSION

CABIN DECOMPRESSION (indicated by a CABIN ALT 8,500 FT light or 10,000 ft cabin altitude aural warning or both).1 . Oxygen Masks — DON AND 100%2 . Oxygen Microphone Switches — MIC OXY MASK3 . Emergency Descent — AS REQUIRED4 . PASS OXY — ON (as required, assure passengers receiving

oxygen)5 . Wheel INPH/MIC Switches — INPH POS (as required)6 . Cabin Altitude Horn — MUTE (as required)7 . Transponder — EMERGENCY CODE (as required)8 . Refer to PRESSURIZATION SYSTEM FAILURE (above) as required

CAB ALT8500 FT

49



EMERGENCY DESCENT

1 . Throttles — IDLE2 . Speedbrakes/Spoilers — DEPLOY3 . Initial Pitch Attitude — 20° DOWN�CaotN�e:� If structural damage is suspected, limit airspeed to a

reasonable value and limit maneuvering loads until damage assessment.

4 . Airspeed — VMO/MMO5 . Transponder — EMERGENCY CODE6 . Passenger Advisory Light — PASS SAFE7 . Autopilot — DISENGAGE (as required)8 . ATC — ADVISE / OBTAIN LOCAL ALTIMETER SETTING9 . Altitude — 15,000 MSL or MINIMUM SAFE ALTITUDE10 . Passengers — BRIEF�Ca�t�ne:� IT IS THE PILOT’S RESPONSIBILITY TO DETERMINE

MINIMUM SAFE ALTITUDE AND TO ENSURE THAT THE AUTOPILOT DOES NOT TURN THE AIRPLANE INTO TRAFFIC OR UNSAFE WEATHER.



AUTOPILOT EMERGENCY DESCENT MODE

Indicates aircraft is on an autopilot controlled emergency descent. Activates if the aircraft is above 34,275 ft MSL and cabin altitude exceeds approximately 13,500 ft with the autopilot engaged. Also triggers the Master Warning system.

1 . Throttles – IDLE2 . Speedbrakes/Spoilers – DEPLOY�Note:� � If the airplane is above 34,275 ft MSL and the autopilot

engaged, it will automatically enter Emergency Descent Mode (EDM) when the cabin altitude exceeds approximately 13,500 ft. The autopilot will initiate a pitch-down left-turn (approximately 90°) maneuver. The flight crew must retard throttles to idle and extend the speed brakes/spoilers. The autopilot will control the descent to MMO/VMO limit and level off at 15,000 ft MSL. The crew must then retract the speed brakes and apply thrust to resume normal flight.

� The autopilot Emergency Descent Mode (EDM) is annunciated by the red EMER DECENT MODE annunciator illumination and the MASTER WARNING RESET will flash.

� The autopilot EDM cannot achieve maximum rate of descent. It is recommended that the autopilot be disengaged and the airplane hand flown if maximum rate-of-descent is required.

ENVIRONMENTAL SYSTEM SMOKE OR ODOR

1 . Isolation Valve — SHUT2 . CAB PAC Switch — OFF; allow enough time to purge

If no purge:

3 . CAB PAC Switch — HIGH4 . CKPT PAC Switch — OFFSee SMOKE REMOVAL (E-59)

EMERG DESCENT

50

CABINSMOKE51



SMOKE REMOVAL

�Note:� No action is normally required; however, if the smoke is intense:1 . Crew Masks — DON AND 100%2 . PASS OXY — ON3 . Assure passengers receiving oxygen.4 . Passenger Advisory Lights — PASS SAFE5 . Pressurization Controls — SET:

AUTO SCHED/ALTITUDE SELECT Switch — ALTITUDE SELECTCabin Altitude — 10,000 FTCabin Rate — MAXIMUMPAC BLD SELECT — HPPAC Switches — HIGH

If smoke does not decrease:

6 . Emergency Dump Switch — DUMP (Normal Electrical Bus)�Note:� Cabin altitude will not exceed 15,000 ft.\

USE OF SUPPLEMENTAL OXYGEN

If cabin altitude below 25,000 ft:

1 . Crew Oxygen Masks – NORMAL; resume at Step 2 (below)

If cabin altitude at or above 25,000 ft:

1 . Crew Oxygen Masks – 100%2 . Crew/Passengers – ENSURE OXYGEN USE3 . Cabin Altitude – CHECK

If passengers on board:

4 . Descend to a Maximum Altitude of 25,000 ft; resume at Step #5 below).

If passengers not on board:

4 . DESCEND TO A MAXIMUM ALTITUDE OF 34,000 FT; RESUME AT STEP #5 BELOW.

5 . FLIGHT ALTITUDE – AS REQUIRED6 . OXYGEN – CHECK ENDURANCE CHART




7 . RANGE – COMPUTE (BASE RANGE ON OXYGEN ENDURANCE, REVISED FUEL FLOW, AND GROUNDSPEED).

�Note:� The oxygen endurance table cockpit masks are assumed to be in NORMAL at 20,000 ft cabin altitude (with a respiratory rate of 10 liters per minute – body temperature saturated) and in 100% at and above 25,000 ft.

Optional Oxygen Mask and 76 cubic-foot CylinderAvailable Time in Hours and Minutes

2 Cockpit

ALTITUDE 0 Cabin 2 Cabin 4 Cabin 6 Cabin 8 Cabin 10 Cabin 12 Cabin 13 Cabin

8,000 8:40 2:47 1:39 1:11 0:55 0:45 0:38 0:35

10,000 9:09 2:50 1:40 1:11 0:55 0:45 0:38 0:35

15,000 10:17 2:56 1:42 1:12 0:56 0:45 0:39 0:36

20,000 11:49 3:03 1:45 1:13 0:56 0:46 0:39 0:36

25,000 5:44 2:21 1:29 1:05 0:52 0:42 0:37 0:34

30,000 7:09 - - - - - - -

35,000 9:41 - - - - - -

37,000 11:46 - - - - - - -

39,000 13:43 - - - - - - -




EMERGENCY PRESSURIZATION ON

Indicates the designated emergency pressurization source is ON.

�Note:� The emergency pressurization will turn ON when either the ENG BLD AIR are positioned to EMER or the cabin altitude is above approximately 13,500 ft.

Emergency Pressurization Valve fails to the ON position:1 . Affected ENG BLD AIR Switch — EMER/THEN ON

If Emergency Pressurization Valve still ON:2 . LH or RH ENG BLD AIR CB (left panel) — PULL

Emergency Pressurization Valve fails to the ON position:3 . Engine Power (affected side) — REDUCE as required4 . Cabin/Cockpit PAC Switches — HIGH5 . Cabin/Cockpit Temperature Select — AUTO COLD6 . Cabin/Cockpit Wemacs — OPEN7 . Cockpit/Aft Divider Doors — OPEN8 . Windshield Bleed Air, Left and Right Wing and Engine Anti-Ice —

OFF (if not in icing conditions)9 . Land as Soon as Practical

OVERPRESSURIZATION

1 . MAN/NORM Switch — MAN2 . UP-DOWN Manual Control — UP3 . Manual Rate Control — INCREASE as required

If still overpressurized:4 . CKPT or CAB PAC Switch — OFF5 . Engine Power — REDUCE as required (on side with operating PAC)

If still overpressurized:6 . Remaining PAC Switch — OFF

If still overpressurized:7 . Oxygen Masks — DON and 100%8 . Oxygen Microphone Switches — MIC OXY MASK9 . Wheel Interphone Microphone Switches — INPH POS10 . PASS OXY — ON (assure passengers receiving oxygen)11 . Emergency Dump Switch — CABIN DUMP12 . Descend

EMERGPRESS ON

LH RH

52



HP PRECOOLER FAILURE

Indicates high pressure bleed air from the designated precooler heat exchanger has exceeded 560°F.

1 . Isolation Valve – SHUT2 . Affected Engine – REDUCE POWER (If situation permits)

If light does not go out or power reduction is not desired:

3 . PAC Bleed Air Select – LP BLEED�Note:� If anti-icing systems are in use, the HP PRECLR O’HEAT

annunciator light may be followed shortly by annunciation of the associated WING ANTI-ICE annunciator light if the appropriate actions are not taken.

PAC OVERHEAT

Indicates environmental control unit package is disabled because of an overheat condition in the compressor turbine.

1 . APU Bleed Air — OFF2 . Affected PAC Switch — OFF, until light goes out, then ON

If light does not go out:

3 . Isolation Valve OPEN4 . PAC Switch (Remaining PAC) — HIGH, if required to maintain

desired cabin pressure altitude.�Note:� The affected PAC will automatically be shutdown when a PAC

overheat occurs. It will remain shutdown until the affected PAC switch is cycled from ON to OFF and back ON with the annunciator extinguished.

HP PRECLRO'HEAT

LH RH

53

PACO'HEAT

CKPT CAB

54



PAC ISOLATION VALVE OPEN

ADVISORY - Indicates the isolation valve between the cockpit and cabin environmental control unit packages is open.

�Note:� Operation above 25,000 ft MSL is prohibited with the isolation valve open and only one engine supplying air to the PACs in HIGH flow mode.

DUCT OVERHEAT

Indicates temperature in the designated heater duct is more than 300°F.

1 . APU Bleed Air — OFF2 . Cockpit or Cabin Temperature CBs (left CB panel) — CHECK, reset

if necessary.

If circuit breakers are closed:

3 . Affected PAC Temperature Select — MANUAL/FULL COLD (leave in this position until light goes out)

If light does not go out:

4 . Affected PAC — OFF5 . Isolation Valve — OPEN6 . PAC Switch (remaining PAC) — HIGH, if required to maintain

desired cabin pressure.

If circuit breaker is open or reopens:

2 . AFFECTED ENGINE — REDUCE POWER (IF SITUATION PERMITS) AND MONITOR SUPPLY AIR TEMPERATURE TO KEEP BELOW 250°F.

If power reduction is not desired:

3 . AFFECTED ENGINE BLEED AIR SWITCH — OFF4 . PAC SWITCH (REMAINING PAC) — HIGH, IF REQUIRED TO

MAINTAIN DESIRED CABIN PRESSURE.

ISO VALVEOPEN

55

DUCTO'HEAT

CKPT CAB

56



PAC HIGH PRESSURE VALVE OPEN

ADVISORY — Indicates the PAC high pressure bleed air valve was either automatically or manually opened.

LIMITATION: � Operation of the cabin and cockpit PACs in high pressure bleed air (PAC HP VLV OPEN) is not approved for takeoff and landing.

� Operation of the cabin and cockpit PACs in high pressure bleed air (PAC HP VLV OPEN) is prohibited when any of the following systems are on:

� Windshield Bleed Air � Wing Anti-Ice � Engine Anti-Ice

PAC HIGH FLOW

ADVISORY — Indicates the Pac High Flow selected.

LIMITATION: � Operation in HIGH mode is not approved for takeoff and landing and flight above FL450.

� Operation in HIGH mode is not approved above FL250 when the isolation valve is open and either left or right engine bleed air switch if OFF.

� Except for Emergency Operations, the HIGH mode is not approved when any of the following systems are on:

� Windshield Bleed Air � Wing Anti-Ice � Engine Anti-Ice

CABIN OR ACCESSORY DOOR UNLOCKED

Indicates one or more accessory doors are not correctly locked.

Continuous illumination on ground:

1 . Correct condition prior to flight

Continuous illumination in flight:

1 . Airspeed — REDUCE2 . Land as Soon as Practical

PAC HPVLV OPEN

LH RH

57

PAC HI58

ACC DOORUNLOCKED

NOSE BAG

59




Momentarily illumination (cycles ON and OFF), ground only:

Indicates failure or improper position of one or more of the cabin door switches.

1 . Correct Condition Prior to Flight

Continuous illumination in flight:

Indicates failure or improper position of one or more of the cabin door pins, or the door handle is not over center.

1 . Cabin Altitude — SELECT 9,500 ft.2 . Airspeed — REDUCE3 . Passenger Advisory Lights — PASS SAFE4 . Cabin Door — KEEP CLEAR5 . Land as Soon as Practical�Note:� If practical, descent to a lower altitude is recommended to

reduce the cabin differential pressure.

CABIN DOOR PRESSURE SEAL FAILURE

Indicates a loss of bleed air to the cabin door primary seal; the secondary door seal should prevent loss of cabin pressure.

1 . Descend to 41,000 ft or lower.2 . Pilot – DON crew oxygen mask (set regulator to normal).3 . Passenger Advisory Light – PASS SAFE4 . Land as soon as practical.

BAGGAGE HEATER OVERHEAT

Indicates baggage heater has exceeded 180°F.

1 . Baggage Heater Switch – OFF

NOISE, SMOKE, OR LACK OF COOLING WITH THE FREON AIR CONDITIONING SYSTEM INSTALLED AND A/C SWITCH ON

1 . Air Conditioning Fan — OFF2 . AFT and FWD EVAP FAN Circuit Breaker — PULL (Left Circuit

Breaker Panel)

CABIN DOORUNLOCK

60

DOORSEAL61

BAG HTRO'HEAT

62




WINDSHIELD FAULT


1 . Correct condition prior to flight.�Note:� Indicates the controller has detected a fault and shut off

the windshield anti-ice. May also be accompanied by corresponding W/S O’HEAT light.

Indication in flight:

2 . Affected Windshield HT Switch – OFF, then ON.

If light remains ON:

3 . Affected Windshield HT Switch – OFF4 . LEAVE Icing Environment

WINDSHIELD OVERHEAT

Indicates a windshield overheat condition. May be accompanied by a W/S FAULT light.

W/S O’HEAT on steady or cycling. W/S FAULT light out:

1 . Windshield Bleed Air Switch — OFF�Note:� Windshield bleed air is used to aid in rain removal and ground

defog.

If light stays ON:

2 . AC Power — MONITOR, note increase/decrease in affected amperage when windshield cycles. If horizontal stabilizer anti-ice is on, turn it off long enough to monitor the windshield, then on.

�Note:� If AC amperage is cycling normally, this indicates failure of the overheat warning system. Windshield is functioning normally.

If amperage is not cycling:

3 . Windshield HT Switch (affected side) — OFF4 . Leave Icing Environment AS SOON AS POSSIBLE

W / SFAULT

LH RH

63

W / SO’HEAT

LH RH

64

A N T I




W/S O’HEAT and W/S FAULT lights cycle (controller failure, system cycling on overtemp limit):

1 . Windshield HT Switch (affected side) — OFF (Unless needed for heavy icing).

2 . Leave Icing Environment AS SOON AS POSSIBLE

W/S O’HEAT and W/S FAULT lights on steady (system failure):

1 . Windshield HT Switch (affected side) — OFF2 . Leave Icing Environment AS SOON AS POSSIBLE�Note:� Ice protection will be lost to the outboard and center sections

of the affected windshield and the inboard section of the opposite windshield.

WINDSHIELD AIR ON WITH WINDSHIELD BLEED AIR SWITCH IN THE OFF POSITION

1 . Windshield Bleed Air Manual Valves — OFF�Note:� Indicates a failure of the windshield flow control shutoff

valve and, if other anti-ice systems are not on, failure of the respective master anti-ice shutoff valve.

COCKPIT FORWARD OR SIDE WINDSHIELD CRACKED OR SHATTERED

1 . Cabin Altitude — SELECT 9,500 ft.2 . Pilot — DON crew oxygen mask (set regulator to normal)3 . Passenger Advisory Light — PASS SAFE4 . Remain clear of/or leave icing conditions.�Note:� Descent to the lowest practical altitude consistent with fuel

range requirements is strongly recommended to reduce cabin differential pressure.

If either forward windshield failed:

5 . Windshield Heat — BOTH SWITCHES OFF6 . Land As Soon As Practical

If one side windshield failed:

5 . WINDSHIELD HEAT — TURN OPPOSITE SWITCH OFF6 . LAND AS SOON AS PRACTICAL

W/S AIR65




WINDSHIELD DEFOG FAN FAILURE OR LOSS OF DEFOG AIRFLOW TO WINDSHIELD

1 . Defog Fan Circuit Breaker (left CB panel) — CHECK IN

If there is still no airflow:2 . Windshield HT — ON

PITOT-STATIC HEATER FAILURE

Indicates pitot or static heater(s) is inoperative. The AOA probe is not monitored by this.

1 . Inoperative System — SWITCH OFF then ON2 . Pitot Static Circuit Breakers (left CB panel) — CHECK

If light remains on:3 . Remaining Airspeed and Altimeter — MONITOR

ENGINE ANTI-ICE FAILURE

Indication that engine inlet anti-ice inoperative or inadequate bleed air heat, DC wing root fairing heater failure, or Pt2/Tt2 heater element failure.

Continuous illumination:

1 . Affected Engine — INCREASE POWER

If light does not go out after increase in power:

2 . Affected Engine Anti-Ice Switch — OFF, note decrease in engine ITT, then ON

�Note:� � Decrease in ITT indicates operational bleed air but probable fairing or Pt2/Tt2 failure. No decrease indicates probable bleed air failure. Pulling the affected engine anti-ice circuit breaker (left CB panel) may cause the bleed air valve to open, but will render the fairing and Pt2/Tt2 anti-ice inoperative.

� Initial illumination of the ENG ANTI-ICE annunciator light is normal after initial system activation. The lights will extinguish as proper operating temperature is attained.

3 . Leave Icing Environment

Cycles ON and OFF:1 . ADVISORY – Indicates failure of the wing fuselage fairing

temperature controller — MONITOR DC AMPERES

P/S HTROFF

LH RH

66

ENGINEANTI-ICE

LH RH

67



WING ANTI-ICE FAILURE

Indicates wing anti-ice system is either overheating or is receiving inadequate bleed air temperature.

Continuous illumination (wing temperature low):

1 . Affected Engine — INCREASE POWER ON CORRESPONDING ENGINE

If light does not go out after increase in power:

2 . Leave Icing Environment�Note:� Initial illumination of the wing anti-ice annunciator light(s) is

normal after initial system actuation. The lights will extinguish as proper operating temperature is attained.

Cycles on and off (wing temperature high):

3 . Affected Wing — REDUCE POWER ON CORRESPONDING ENGINE (if situation permits)

�Note:� If the bleed air supply temperature to the wing is excessive, the wing anti-icing will automatically cycle off until the wing temperature is reduced, at which time the bleed air will be cycled back on. The corresponding HP PRECLR O’HEAT annunciator may also be illuminated.

HORIZONTAL STABILIZER ANTI-ICE FAILURE OR ICE SUSPECTED TO BE ON THE HORIZONTAL STABILIZER

Continuous (single or dual) light illumination (from either a failed alternator or an engine shutdown):

1 . Horizontal Stabilizer Anti-Ice CBs (LH Panel) — CHECK (only one reset attempt)

2 . AC Power — CHECK affected AC Voltage and Amperage. (Greater than 9 amps if electronic windshield is ON).

�Note:� Illumination of the STAB ANTI-ICE lights may occur after initial system actuation during extremely cold ground ambient air conditions. The lights will extinguish as proper operating temperature is obtained.

WINGANTI-ICE

LH RH

68

STABANTI-ICE

LH RH

69




3 . Horizontal Stabilizer Switch(es) (affected side) — OFF THEN ON

If one light still illuminated - after confirming proper AC voltage and amperage:

4 . Horizontal Stabilizer Anti-Ice Switch (affected side) — OFF5 . Leave Icing Environment�Ca�t�ne:� � EXTENDING THE FLAPS TO THE FULL POSITION

COULD RESULT IN THE AIRCRAFT PITCHING DOWN.

� IF THERE IS A REDUCTION OF ELEVATOR CONTROL WHEEL BACK PRESSURE AS THE FLAPS ARE EXTENDED FROM THE 20° TO FULL POSITION, IMMEDIATELY RESELECT 20° FLAPS AND TRIM NOSE DOWN APPROXIMATELY 1°.

�CaotN�e:� After having an icing encounter with one horizontal stabilizer leading edge anti-ice system inoperative, the flaps must not be extended beyond the 20° position for landing.

6 . Landing — Refer to Normal Procedures for landing with flaps at 20° position.

If both lights still illuminated or ice suspected on horizontal stabilizer leading edges:

4 . LEAVE ICING ENVIRONMENT�Ca�t�ne:� � EXTENDING THE FLAPS BEYOND THE 7° POSITION

COULD RESULT IN THE AIRCRAFT PITCHING DOWN.

� IF THERE IS A REDUCTION OF ELEVATOR CONTROL WHEEL BACK PRESSURE AS THE FLAPS ARE EXTENDED PAST 7°, IMMEDIATELY RESELECT 7° FLAPS AND TRIM NOSE DOWN APPROXIMATELY 1°.

�CaotN�e:� � Ice may remain on the horizontal stabilizer leading edge after an inadvertent Icing encounter. This condition may occur even if the horizontal stabilizer anti-ice has been subsequently been turned on. In this case, the flaps must not be extended beyond the 7° position for landing.

� After having an icing encounter with both horizontal stabilizer leading edge anti-ice system inoperative or ice suspected on the horizontal stabilizer, the flaps must not be extended beyond the 7° position for landing.





5 . LANDING — REFER TO LANDING WITH FLAPS UP OR AT 7° POSITION (E-49)

Momentary Light Illumination (Cycles ON and OFF):

Advisory – Indicates failure of the normal temperature controller.




HYDRAULIC SYSTEM

ON

OFF

NORM

P

SPOILERHOLD DOWNACCUMULATOR1,500 PSINITROGENPRECHARGE

NWSACCUM

P

P

P

LOW FLUID LEVELSHUTOFF VALVE150 IN3

FIREWALLSHUTOFF

ENGINE-DRIVENPUMP3,000 PSI

APUPUMP3,000 PSI

150 IN3

PRESSURE-OPERATEDRESERVOIR

FIREWALLSHUTOFF

HYD VOLLOW

HYD PRESSLOW

ENGINE-DRIVEN

PUMP3,000 PSI

AUXPUMP3,000 PSI

BOOTSTRAPPRESSURE

2,400 PSI

SPEEDBRAKES

LNDG GEAR

AILERONS

GROUND SPOILERS

WHEELBRAKES

ROLLSPOILERS

GROUNDSERVICEQUICKDISCONNECT

FILTER

MAINSYSTEM

RELIEFVALVE

3,450

BATTERY BUS

LH ENGINEFIREPUSH RH ENGINE

FIREPUSH

HYD F/WSHUTOFF

LH RH

PRESSURETRANSDUCER

SHUTTLEVALVE

XOVR RIGHT FEED BUSLEFT CB PANEL

LEFT FEED BUSLEFT CB PANEL

AUXSYSTEMRELIEFVALVE3,450PSID

AUX HYDPUMP ON

1,200 PSI

THRUST REVERSERS

NOSEWHEEL STEERING

MAIN SYSTEM PRESSURE

HYDRAULIC RETURN

AUX HYDRAULIC PUMP PRESSURE

RESERVOIR FLUID

1,500 PSI NITROGEN PRECHARGE

LH RH

HOLD DOWNSPOILER

1,500 PSINITROGEN

PRECHARGE

MAINSYSTEM

ACCUMULATOR

PSID

G E A R / H Y D



LANDING GEAR WILL NOT EXTEND

Airspeed below 210 KIAS1 . Landing Gear Handle — DOWN (airspeed below 210 KIAS)2 . Gear Control Circuit Breaker (left CB panel) — CHECK IN3 . Auxiliary Gear Control T-Handle — PULL (rotate clockwise to lock)

If auxiliary gear control T-handle cannot be pulled:

� Gear Retract Hydraulic Shutoff Valve (located in aft cabin) — PULL

� Auxiliary Gear Control T-Handle — PULL (rotate clockwise to lock)

4 . Rudder — YAW AIRPLANE (if necessary to achieve downlock lights)

5 . Auxiliary Gear Control Knob — PULL to blow down (for positive gear lock)

6 . Landing Gear — CHECK DOWN and LOCKED7 . Auxiliary Gear Control Knob — PUSH IN TO STOW8 . Auxiliary Gear Control T-Handle — ROTATE COUNTERCLOCKWISE

and PUSH IN TO STOW

HYDRAULIC WHEEL BRAKE FAILURE

1 . Brake Pedals — REMOVE FEET2 . Emergency Brake Handle — PULL and MODULATE AS REQUIRED3 . Landing Distance — Multiply by 1.6�Note:� The anti-skid brake system does not function during

emergency braking. Excessive pressure on emergency brake handle can cause all wheel brakes to lock resulting in blowout of all main wheel tires. Repeated application and release may cause premature loss of pneumatic pressure.

ANTI-SKID SYSTEM FAILURE

Indicates failure of the anti-skid system or is OFF.

1 . Anti-Skid Switch — TEST / THEN ON2 . Anti-Skid Circuit Breaker (left CB panel) — RESET

ANTISKID

70




If annunciator remains illuminated:

3 . Anti-Skid Switch — OFF4 . Landing Distance — Multiply by 1.6�Note:� The power brakes system is operative. Excessive brake

pressure can cause all wheel brakes to lock resulting in blowout of all main wheel tires.

If annunciator illuminated on ground:

Refer to Supplement 11 - DISPATCH WITH ANTI-SKID SYSTEM OFF

NOSE WHEEL STEERING MALFUNCTION

1 . AP/TRIM/NWS Disconnect Button — PRESS2 . Directional Control — MAINTAIN BY DIFFERENTIAL BRAKING AND

RUDDER

HYDRAULIC SYSTEM FAILURE

Indicates the designated hydraulic pump pressure is less than 2,400 PSI.

Indicates the fluid reservoir fluid level 150 cubic inches.

Indicates the spoiler hold down has activated either manually or automatically (Hyd Press 1,200 PSI).

Indicates the Aux Hyd Pump has activated either manually or automatically (Hyd Press 1,500 PSI).

HYD VOL LOW and/or BOTH HYD PRESS LOW LIGHTS ON1 . Airplane Altitude FL450 (maximum) — DESCEND as required2 . Spoiler Hold Down Switch — ON, Check spoiler hold down light

ON3 . Auxiliary Hydraulic Power Switch — VERIFY NORMAL4 . Hydraulic Volume — MONITOR

If hydraulic volume continues to decrease (below 150 cubic inches):

5 . Auxiliary Hydraulic Power Switch — OFF6 . Land as Soon as Practical�CaotN�e:� Roll Spoilers will be inoperative with the Spoiler Hold

Down ON and Aux Hyd Power OFF. Limiting crosswind component is 10 Kts.

HYD PRESSLOW

LH RH

71

HYD VOLLOW

72

SPOILERHOLDOWN

73

AUX-HYDPRESS

74





�Note:� If the auxiliary hydraulic pump is OFF the following conditions apply:

� The auxiliary hydraulic system will not pressurize the spoiler hold down line. Spoiler hold down line is supplied only by accumulator pressure.

� The spoilers may float up causing a reduction in planned range of approximately 5% due to increased fuel flow and/or decrease in airspeed if the spoiler hold down light is not on.

� The anti-skid/power brake system will be inoperative. Plan to use emergency brakes.

� The roll spoilers will be inoperative. Lateral control is sufficient for a maximum sideslip of one-half ball.

If hydraulic volume stabilizes at approximately 150 cubic inches:

6 . AUXILIARY HYDRAULIC POWER SWITCH — ON; CHECK FOR FLUID VOLUME LOSS

7 . LAND AS SOON AS PRACTICAL�Note:� � The auxiliary hydraulic pump should activate and the roll

control spoilers should be operative with the auxiliary hydraulic power switch on or normal if volume stabilizes at 150 cubic inches.

� The landing gear, speedbrakes, spoilers, aileron boost, thrust reversers, and thrust reverser emergency stow will be inoperative.

� Wheel Brakes, Spoiler Hold Down, and Roll Spoilers will be operative with the auxiliary system activated.

Before landing:

1 . Landing Data — CONFIRM � VAPP (per landing flap schedule) — +15 KIAS with spoiler hold

down light OFF � VREF (per landing flap schedule) — +15 KIAS with spoiler hold

down light OFF � Takeoff Thrust Fan Speed (N1) � Compute Landing Distance from Chart:





Auxiliary Hydraulic Pump/Field Pressure Altitude

Spoiler Hold DownAnnunciator

Illuminated Extinguished

Pump ON 1 .25

Pump OFF 2 .25

Pump OFF/8,000 ft and below 3 .00

Pump OFF/Above 8,000 ft 3 .75

�Ca�t�ne:� THE CREW MUST CONFIRM SPOILER HOLD DOWN LIGHT IS EITHER ILLUMINATED OR EXTINGUISHED TO FLY PROPER AIRSPEED SCHEDULE.

�Ca�t�ne:� LANDING WITH A TAILWIND OR NEGATIVE (DOWNHILL) RUNWAY GRADIENT IS PROHIBITED WITH THE SPOILER HOLD DOWN LIGHT OFF.

2 . Avionics and Flight Instruments — CHECK and SET3 . Radio Altimeter — SET4 . Fuel Transfer — OFF (wing and fuselage)5 . Engine Synchronizer — OFF6 . External Lights — AS REQUIRED7 . Flaps — AS REQUIRED8 . Ignition — ON9 . Passengers — BRIEF10 . Seats, Seat Belts and Shoulder Harnesses — SECURE11 . Passenger Advisory Lights — PASS SAFE12 . Landing Gear — DOWN and LOCKED

If landing gear will not extend: � Landing Gear Handle — DOWN (airspeed below 210 KIAS) � Gear Control CB — CHECK IN � Auxiliary Gear T-Handle — PULL/ROTATE CLOCKWISE TO

LOCK

If landing gear will not extend:

� Gear Retract Hydraulic Shutoff Valve (located in aft cabin) — PULL

� Auxiliary Gear Control T-Handle — PULL (rotate clockwise to lock)

� Rudder — YAW AIRCRAFT (if necessary to achieve downlock lights)

� Auxiliary Gear Control Knob — PULL to blow down (for positive gear lock)

� Landing Gear — CHECK DOWN AND LOCKED � Auxiliary Gear Control Knob — PUSH IN TO STOW � Auxiliary Gear Control T-Handle — ROTATE

COUNTERCLOCKWISE and PUSH IN TO STOW





13 . Nose Wheel Steering Switch — PUSH (Verify ARMED light is ON)14 . Annunciator Panel — CHECK15 . Autopilot and Yaw Damper — CHECK�Ca�t�ne:� IF AUXILIARY HYDRAULIC PUMP IS OFF BECAUSE

OF CONTINUED HYDRAULIC VOLUME LOSS, THE HYDRAULIC WHEEL BRAKE SYSTEM WILL BE INOPERATIVE.

�Note:� If the speedbrakes/spoilers are floating up because of a loss of accumulator pressure, the no takeoff warning will sound as the aircraft descends below 500 ft AGL.

Landing:

16 . Throttles — IDLE17 . Brakes — APPLY (after nose wheel contact) as follows:

If auxiliary hydraulic power on:

� Brake Pedals — USE

If auxiliary hydraulic power off or brake pressure fades:

� Brake Pedals — REMOVE FEET FROM BRAKE PEDALS � Emergency Brake Handle — PULL and MODULATE as required

�Note:� The anti-skid brake system does not function during emergency braking. Excessive pressure on the emergency brake handle can cause all wheel brakes to lock resulting in main wheel tire blowout. Repeatedly applying and releasing brakes may cause premature depletion of pneumatic pressure.

HYDRAULIC FLUID TEMPERATURE LOW

Indicates one or more of the hydraulic temperature sensors may have activated because ambient temperature is at or below -33°F.


1 . Hydraulic Temperature Monitor Reset Switch — PUSH AFTER LIGHT EXTINGUISHES. After one or both engines (or the optional APU hydraulic pump) have run for approximately 10 minutes.

75HYD TEMP

LOW





�Note:� � The hydraulic temperature monitor box (BITE indicator) is in the tailcone below the engine synchronization control box.

� The reset clears the BITE indicators which may have been activated.

� The engine run time may be longer due to colder ambient temperature and the length of time that the airplane has been exposed to the cold soak conditions.

If condition cannot be corrected on ground:

2 . Airplane may be dispatched provided that the INDICATION IN FLIGHT procedures are followed.

Indication in flight:

1 . Speedbrakes — SLOWLY DEPLOY TO 20%; THEN STOW

If light remains on:

2 . Speedbrakes/Spoilers — USAGE IS PROHIBITED3 . Airplane Altitude — FL450 MAXIMUM; descend as required4 . Aural Warn Circuit Breaker #2 (left CB panel) — CHECK IN

If light extinguishes:

5 . Speedbrakes/Spoilers — USAGE IS APPROVED6 . Altitude Restriction — REMOVED�Note:� The HYD TEMP LOW light may go out due to descending into

warmer ambient temperature.

Post flight inspection of bite indicators (leave electrical power on):

1 . Hydraulic Temperature Monitor BITE Indicator — RECORD BITE(s) which were activated during the flight.

2 . Hydraulic Temperature Monitor Reset Switch — PUSH; verify the BITE indicator has reset.





AUXILIARY HYDRAULIC POWER ON

Indicates the electrically driven hydraulic pump is ON.

�Note:� � The auxiliary hydraulic power will come on under one of the following conditions:

� Turning the auxiliary hydraulic power switch to ON.

� Hydraulic system low pressure (less than 1,500 PSI) and the auxiliary hydraulic power switch in NORM.

� Spoiler hold down switch ON and auxiliary hydraulic power switch in NORM.

1 . AUX Hydraulic Power Switch, Hydraulic Pressure/Volume, and Spoiler Hold Down Switch — CHECK

PARKING BRAKE ON

Indicates the airplane parking brake is ON.

1 . Parking Brake — CHECK handle is full down

AUX-HYDPRESS

76

PARKBRAKE

77



EFIS RED GUN FAILURE

The failure of a red gun in an electronic display indicator results in the following presentations:

EADI– Sky turns from dark blue to a dull dark blue– The ground turns from brown to a green hue– Caution annunciations turn from amber to green

EHSI– Caution annunciations turn from amber to green

1 . Use Display with Caution — MONITOR remaining displays for any red annunciators

�Ca�t�ne:� FOLLOWING FAILURE OF A RED GUN IN A DISPLAY UNIT, THE RED WARNING ANNUNCIATORS WILL NOT BE VISIBLE.

SYMBOL GENERATOR FAILURE

EADI A symbol generator failure is indicated by red SG FAIL or loss of both EADI and EHSI displays

EHSI

Airplanes with operative optional MFD:

1 . MFD Mode Selector (Outer Concentric) Knob — FULL counterclockwise for pilot’s SG backup or full clockwise for copilot’s SG backup

2 . EADI Display (Selected Side) — VERIFY “SG” annunciator�Note:� � All functions and operations on the side with the failed

symbol generator remain unchanged.

� The MFD display is blanked during periods of symbol generator backup.

Airplanes without (or with inoperative) optional MFD:

1 . SYM GEN REV Button (Affected Side) — PUSH; verify SG1 or SG2 is displayed in the pilot’s and copilot’s EADIs

2 . HSI SEL Button — PUSH (if required) to select same side as operating symbol generator

78

79

A V N




�Note:� � SG1 or SG2 indicates cross-side symbol generator is driving the displays.

� Flight director modes are cleared when both SG REV and flight director are on the same side. Reselect desired flight director modes.

� Only the display controller on the same side as the operating symbol generator is functioning. The cross-side VHF NAV cannot be displayed on either EFIS but can be displayed on the RMIs and the Pilot’s standby OBS (NAV 1 only).

EADI FAILURE

1 . EADI Dim (Outer Concentric) Knob — TURN to OFF position; composite mode is displayed on EHSI. Flight Director required.

To obtain EHSI data (if desired when optional MFD is installed):

2 . MFD Mode Selector (Outer Concentric) Knob — Counterclockwise for pilot’s EHSI display or clockwise for copilot’s EHSI display

�Note:� � All operations using the EHSI display, except for dimming, are unchanged.

� All functions of the MFD controller are inoperative except for dimming when the MFD mode selector knob is in the EHSI backup position.

EHSI FAILURE

1 . EHSI Dim (Outer Concentric) Knob — TURN to OFF position; composite mode is displayed on EADI. Flight Director required.

�Note:� The MFD is blanked when the HSI dim knob is turned to OFF and if the optional MFD mode selector knob is to HSI.




EFIS OR OPTIONAL MFD FAN LIGHT ILLUMINATES

Indicates EFIS and/or avionics bay cooling fan failure.

Indicates MFD cooling fan failure.

On ground:

1 . Circuit Breakers — PULL the following applicable breakers in the right hand circuit breaker panel: EFIS 1, EADI 1 AND EHSI 1; or EFIS 2, EADI 2 and EHSI 2; or MFD SYM GEN and MFD IND

2 . Ground Operating Time — 10 Minutes3 . Prior to Takeoff — REINSTATE the Circuit Breakers that were pulled�CaotN�e:� Power must be removed and remain OFF to prevent the

EFIS or MFD systems from overheating.

On flight:

1 . Cockpit Temperature — MAINTAIN BELOW 80°F�Note:� The EFIS system has been shown not to overheat in flight

with a failed cooling fan with cockpit temperatures below 80°F.

SINGLE AIR DATA COMPUTER FAILURE

Indicated by loss of affected side airspeed and altitude. Pilot’s altimeter (if affected) will revert to pneumatic mode.1 . Airspeed and Altitude — USE OPPOSITE SIDE2 . Transponder Altimeter Select Switch — SELECT OPPOSITE AIR

DATA, PRI/SEC (PILOT’S/COPILOT’S)

If pilot’s Air Data Computer inoperative:

3 . Pilot’s Altimeter — USE COPILOT OR STANDBY ALTIMETER (Copilot’s air data instruments and pilot’s standby airspeed and pneumatic altitude are available)

�Note:� If operating in RVSM airspace take appropriate actions.

EFIS FAN80

MFD FAN81



DUAL AIR DATA COMPUTER FAILURE

Indicated by loss of pilot’s and copilot’s airspeed and altitude indications. Pilot’s altimeter will revert to pneumatic mode.1 . Airspeed — USE STANDBY INDICATOR (observe placard VMO

schedule)2 . Pilot’s Altimeter — SELECT PNEUMATIC MODE (copilot’s airspeed

and altitude will be inoperative)3 . Refer to AHRS MODE�Note:� � Both AHRS revert to basic mode

� Transponder altitude reporting inoperative

� Autopilot only operates in basic attitude hold

� Pilot’s standby airspeed and pneumatic altitude are the only air data sources

AHRS BASIC MODE

Illuminates with a dual Air Data Computer (ADC) failure or loss of True Airspeed (TAS) input from ADCs.

1 . Vertical Gyro Switch (affected side) — FAST POSITION FOR 10 SECONDS/ RELEASE (one side at a time if dual) repeat as frequently as required

� Aircraft must be in level unaccelerated flight � ATT flag appears and all altitude data is removed from display

while switch is in FAST � Verify new indicated altitude on EADI is reasonable


AHRS DC POWER LOSS

ADVISORY — Indicates AHRS 1 or 2 has transferred to the auxiliary battery due to loss of DC power.

SINGLE AHRS FAILURE

1 . HDG REV and ATT REV Buttons (affected side) — PUSH; verify MAG 1 or 2 and ATT 1 or 2 is displayed in both the pilot’s and copilot’s displays.

�CaotN�e:� Heading and attitude comparator monitor functions will not be available. Monitor standby flight instruments.

AHRSBASIC

A B

82

AHRS83AUX PWR



HEADING FAILURE

1 . HDG REV Button (affected side) — PUSH; verify that MAG 1 or 2 is displayed in both the pilot’s and copilot’s display. Heading comparator monitor will not be available.

ATTITUDE FAILURE

1 . ATT REV Button (affected side) — PUSH; verify ATT 1 or 2 is displayed in both the pilot’s and copilot’s displays. Altitude comparator monitor will not be available.

COMPARISON MONITOR

One or more of the following parameters has exceeded its predetermined tolerance level:

Pitch Attitude PIT Roll Attitude ROL Heading HDG Localizer or Azimuth LOC or AZ Glideslope or Glide path GS or GP Pitch and Roll Attitude ATT Localizer and Glideslope ILS or MLS1 . CMPRTR WARN LIGHT / SWITCH — PUSH and hold until all

annunciators in both the pilot’s and copilot’s EADI’s and CMPRTR WARN extinguish.

FLIGHT GUIDANCE COMPUTER FAILURE

1 . AFCS A or B On Switch — VERIFY OPPOSITE GREEN LIGHT ILLUMINATED

2 . AFCS Reset Switch — PUSH A OR B (affected side, may require 10 seconds to reset)

3 . FD OFF Message (affected side EADI) — VERIFY EXTINGUISHED4 . AFCS A or B On Switch (affected side) — PUSH (verify AFCS A or B

green ON light illuminated).

CMPTRWARN

84

FAIL A

RESET

85 AFCS A

ON

86 AFCS B

ON

87 FAIL B

RESET

88



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c7_oh

Documents

icing encounters

severe icing conditions2

operating procedure

nearest suitable airport

practical tool

landingicing conditions

excessive maneuvering

control problems