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COURSEWARE SUPPORTHURST 8900 Trinity Blvd. Hurst, Texas 76053 (817) 276-7500 Fax (817) 276-7501

CITATIONJET 525 PILOT TRAINING MANUAL VOLUME 1

Record of Revision No. 3

This is a revision of the CitationJet 525 Pilot Training Manual.A solid vertical line in the margin indicates the content of theadjacent text or figure has been changed. A vertical line adja-cent to a blank space indicates material has been deleted.Any page affected by the revision is marked Revision 3 in thelower left or right corner. If a page has Revision 3 in the lowerleft or right corner and no vertical line in the margin, it is a pagein which format only has been changed.The changes made in this revision will be further explained atthe appropriate time in the training course.

FlightSafetyinternational

the best safety device in any aircraft is a well-trained crew. . .


CITATIONJET 525PILOT TRAINING MANUAL

VOLUME 1OPERATIONAL INFORMATION

FlightSafety International, Inc.Marine Air Terminal, LaGuardia Airport

Flushing, New York 11371(718) 565-4100

www.flightsafety.com

Courses for the CitationJet CE-525 aircraft are taught at the followingFlightSafety Learning Centers:

Citation Learning CenterFlightSafety International1851 Airport RoadPO Box 12323Wichita, Kansas 67277(316) 220-3100(800) 488-3214FAX (316) 220-3134

San Antonio Learning CenterSan Antonio International Airport9027 Airport BoulevardSan Antonio, Texas 78216-4806(210) 826-6358(800) 889-7917FAX (210) 826-4008

Copyright 1999 by FlightSafety International, Inc.All rights reserved.

Printed in the United States of America.

FOR TRAINING PURPOSES ONLY

FOR TRAINING PURPOSES ONLY

NOTICEThe material contained in this training manual is based on infor-mation obtained from the aircraft manufacturers Pilot Manualsand Maintenance Manuals. It is to be used for familiarizationand training purposes only.

At the time of printing it contained then-current information. Inthe event of conflict between data provided herein and that inpublications issued by the manufacturer or the FAA, that of themanufacturer or the FAA shall take precedence.

We at FlightSafety want you to have the best training possible.We welcome any suggestions you might have for improving thismanual or any other aspect of our training program.

CONTENTSEXPANDED CHECKLIST

Normal Procedures

Abnormal Procedures

Emergency Procedures

LIMITATIONS

MANEUVERS AND PROCEDURES

WEIGHT AND BALANCE

PERFORMANCE

CREW RESOURCE MANAGEMENT

RECURRENT

Recurrent Syllabus

Systems Review

Master Warning Systems

EXPANDED CHECKLISTSCONTENTS

NORMAL PROCEDURES ................................................................ NP-iABNORMAL PROCEDURES........................................................... AP-iEMERGENCY PROCEDURES......................................................... EP-i

FOR TRAINING PURPOSES ONLY EC-i


CITATIONJET 525 PILOT TRAINING MANUAL

NORMAL PROCEDURESCONTENTS

PagePREFLIGHT........................................................................................ NP-1

Preflight Inspection................................................................... NP-1Preliminary Cockpit Inspection ................................................ NP-1Exterior Inspection.................................................................... NP-3Cabin Inspection ..................................................................... NP-12Cockpit Inspection .................................................................. NP-13

NORMAL PROCEDURES.............................................................. NP-15Quick Turnaround................................................................... NP-15Before Starting Engines.......................................................... NP-16Starting Engines...................................................................... NP-17Before Taxiing ........................................................................ NP-20Taxiing .................................................................................... NP-23Before Takeoff ........................................................................ NP-25Takeoff .................................................................................... NP-27After TakeoffClimb............................................................. NP-28Cruise...................................................................................... NP-29Descent ................................................................................... NP-30Approach................................................................................. NP-32Before Landing ....................................................................... NP-34Landing ................................................................................... NP-36All Engines Go-Around.......................................................... NP-38After Landing.......................................................................... NP-38Shutdown ................................................................................ NP-39Turbulent Air Penetration ....................................................... NP-41

Revision 3 FOR TRAINING PURPOSES ONLY NP-i



NORMAL PROCEDURESPREFLIGHTPREFLIGHT INSPECTION

1. Battery ................................................................................. CONNECTED

2. Engine/Pitot Covers................................................ REMOVED (2 EACH)

PRELIMINARY COCKPIT INSPECTIONNOTE

FAA regulations require a flashlight and first aid kitbe carried. Check that oxygen masks, headsets, mi-crophones, and the pilots checklists are on board.

Prior to cockpit inspection, check tailcone to ensurebattery is connected.

To be displayed in the airplane at all times:

1. Documents.................................................................... CHECK ABOARD

A preliminary cockpit inspection should be made on the first flight of theday. Ensure that the airworthiness and registration certificates andtransmitter license(s) are displayed in the airplane. The FAA-approvedAirplane Flight Manual, Honeywell SPZ 5000 IFCS Pilots Manual, theapplicable FMS Pilots Manual, radar manual, etc. must be carried in theairplane at all times.

2. Flashlight .................................................................................... ABOARD

3. Portable Fire Extinguisher.............................. SERVICED AND SECURE

Located in a quick-release holder on the floor inboard of the copilots seat,the pressure gage should read in the green arc indicating a 150 psi charge.

4. Microphones, Headsets, and Oxygen Masks.............................. ABOARD

5. Oxygen Quantity............................................................................ CHECK

Check the quantity gage at 1600-1800 psi and crew masks connected tothe side console outlets. Pilots side console oxygen control valve properlypositioned to NORMAL. Caution should be exercised as inadvertentlyplacing the oxygen control valve to MANUAL DROP will result indeployment of the cabin masks. The standard crew masks must be worn

FOR TRAINING PURPOSES ONLY NP-1





NP-2 FOR TRAINING PURPOSES ONLY Revision 3

around the neck for flight above FL 250. The optional crew masks must bestowed in the quick donning holder and set on 100% for flight above FL 250.

The crew can verify oxygen flow by donning the mask with the regulatorin the 100% position and ensuring that no restrictions to breathing arepresent.

6. Control Lock.......................................................................... UNLOCKED

Control surfaces should be free for exterior inspection.

7. Landing Gear Handle ...................................................................... DOWN

8. Elevator Trim................................... POSITION TRIM TAB INDICATORWITHIN TAKEOFF TRIM RANGE

9. Flap Handle................................................................. CHECK POSITION(Agrees with indicated flap position.)

10. All Circuit Breakers ....................................................................... CHECK

11. Generators........................................ GEN (OFF, IF EXTERNAL POWERIS TO BE USED FOR START)

12. All Other Switches............................................................ OFF OR NORM

13. Throttles ............................................................................................... OFF

14. Battery Disconnect Switch ...................................................... BATT DISC

15. Battery Switch ............................... BATT (NO VOLTAGE INDICATION)

16. Battery Disconnect Switch ..................... NORM (24 VOLTS MINIMUM)

17. Fuel Quantity ................................................................................. CHECK

18. Engine Anti-ice Switches....................... ENG ON30 SECONDSOFF(IGNITERS WILL FIRE)

19. Pitot & Static Heat Switch .............................. ON30 SECONDSOFF

Allow 30 seconds for pitot tubes, static ports, and AOA to heat, then OFF.

Confirm LH and RH pitot/static and AOA heater fail lights went out (ON)and come on (OFF) correctly.

20. Landing Lights.......................... ON (CHECK ILLUMINATION ON THEGROUNDOFF, IF SEEN FROM COCKPIT)

21. Other External Lights and Passenger Advisory Lights.......................... ON(CHECK ILLUMINATION OFF,

IF SEEN FROM COCKPIT)

NOTEExpedite all checks with electrical power on and en-sure that the air-conditioner switch is OFF, if an ex-ternal power unit is not used.

Landing and nav lights may be omitted if night flightis not anticipated.

External power must be disconnected to completeitems 14, 15, and 16. Voltmeter will indicate exter-nal power unit voltage, if used, when the batteryswitch is placed in BATT position, item 15.

EXTERIOR INSPECTIONDuring inspection, make a general check for security, condition, and clean-liness of the aircraft and components. Check particularly for damage, fuel,oil, hydraulic fluid leakage, security of access panels, and removal of keysfrom locks.

Hot Items/Lights.......................................................................................... CHECK

1. Left and Right Static Ports ...................................... CLEAR AND WARM

At high outside temperatures it is difficult to feel heat from the static port.Running the back of a finger from the airplane skin over the static port andonto the skin again is the easiest way to sense the higher temperature ofthe port.

2. Left and Right Pitot Tubes.......................................... CLEAR AND HOT

Do not grasp the pitot tube firmly as severe burns may result.

3. Landing Lights ...................................... BOTH ON (IF NOT OBSERVEDFROM THE COCKPIT)

4. Angle-Of-Attack Vane ................................................... FREE AND HOT

Use caution in checking the vane when it is hot. Check for freedom ofmovement.

5. Flashing Beacon ....................................... ON AND FLASHING (IF NOTOBSERVED FROM COCKPIT)

6. Emergency Exit Light........ ON (IF NOT OBSERVED FROM COCKPIT)

Revision 3 FOR TRAINING PURPOSES ONLY NP-3





7. Right Navigation and Strobe Lights................. ON (IF NOT OBSERVEDFROM COCKPIT)

8. Right Pylon Inlet ............................................................................ WARM

9. Tail Navigation Light............................................................................. ON

10. Left Pylon Inlet ............................................................................... WARM

11. Left Wing Inspection, Navigation and Strobe Lights ............. ON (IF NOTOBSERVED FROM COCKPIT)

12. Lights and Battery Switches................................................................. OFF

Station ALeft Nose .................................................................................................... CHECK

1. Baggage Door ......................................................... SECURE AND LOCK

Check latches firmly closed. The baggage and avionics bay doors must bekey locked to actuate the door locked microswitches. The DOOR NOTLOCKED annunciator will not extinguish if the baggage doors are notlocked.

2. Nose Gear, Doors, Wheel, and Tire............. CONDITION AND SECURE

Chine and tread of the nose tire must be in good condition to meet thewater/slush runway operating limitations. Nose tire inflation pressure is120 5psi. On the ground, the two forward gear doors are closed, but therear door is open, allowing a visual inspection of the nose gear assembly,shimmy damper, and nose gear steering bellcrank. Proper nose oleo strutextension of a fully fueled airplane is approximately 2.5 inches.

3. Avionics Bay Latches................................................................... SECURE


Stations B and CRight Nose and Fuselage Right Side........................................................... CHECK

1. Windshield Alcohol Reservoir Sight Gage ..................... FLUID VISIBLE

The ball should be at the top of the sight gage.

2. Brake and Gear Pneumatic Pressure Gage............................ GREEN ARC

The pressure should read between 1,800 and 2,050 psi.

3. Power Brake Accumulator Charge........................... LIGHT GREEN ARCOR DARK GREEN ARC

Light green arc indicates precharged pressure, while a dark green arcindicates operating pressure if battery was turned on and the brake systemcircuit breaker was in during the cockpit inspection.




A

B

C

D

EF

G

H



4. Brake Fluid Reservoir Sight Gages ................................. FLUID VISIBLE

The metal star in the upper sight gage will have a purple tint when thereservoir is full. The ball should be at the top of the upper sight gage if theannunciator charge is in the light green arc (discharged).

5. Baggage Door.................................................... SECURE AND LOCKED

Check latches firmly closed. The baggage doors must be key locked toactuate the door locked microswitch. The DOOR NOT LOCKEDannunciator will not extinguish if the baggage doors are not locked.

6. Oxygen Blowout Disc .................................................................... GREEN

The green disc should be in place. If it is missing, the oxygen bottle maybe empty.

7. Overboard Vent Lines..................................................................... CLEAR

Check vacuum vent, brake reservoir vent, alcohol bottle vent, and gear andbrake air bottle vent.

8. Shadin Temp Probe (if installed) ................................................... CHECK

9. Landing Light........................................................................ CONDITION

10. Top and Bottom Antennas........................... CONDITION AND SECURE


ACCUMULATORDISCHARGED

Fluid visible at topof upper gage

Fluid visiblein upper gage

Fluid level not visiblein upper gage

ACCUMULATORCHARGED

Fluid visible at bottomof upper gage

Fluid above topof bottom gage

Fluid at or belowtop of bottom gage

STATUS

Normal minimum full

Refill when practical

Refill before operation

Station DRight Wing................................................................................................... CHECK

1. Wing Leading Edge Vent................................................................ CLEAR

2. Fuel Quick Drains....... DRAIN AND CHECK FOR CONTAMINATION

Push straight up on the drains when taking fuel samples. The drain maylock open if it is turned.

3. Main Gear Door, Wheel and Tire................ CONDITION AND SECURE

Check tire for wear and inflation to 98 5psi; and the door for security.Check wheel hubcap for condition and security of fastening. Check gearfor general security, fluid leakage, and an approximate oleo strut extensionof 2.5 inches if the airplane is fully fueled.

4. Engine Air Inlet .............................................................................. CLEAR

5. Engine Fan Duct and Fan ........................ CHECK FOR BENT BLADES,NICKS, BLOCKAGE OF FAN

STATORS, AND FOREIGN OBJECTS

If the fan is windmilling, place hand on the bullet nose or install the enginecover to stop the rotation. If damage is observed, refer to the FJ44-1AEngine Maintenance Manual. (Remove cover if installed.)

6. Pylon Inlet ...................................................................................... CLEAR

7. Generator Cooling Air Inlet ........................................................... CLEAR

8. Cabin Escape Hatch ..................................................................... SECURE

9. Stall Strip................... CONDITION (NO NICKS OR DENTS), SECURE

10. Heated Leading Edge.......................... CONDITION, EXHAUST CLEAR

11. Fuel Tank Vent................................................................................ CLEAR

If the vent is blocked, a negative pressure may build up in the wingcausing the tank to collapse.

12. Fuel Filler Cap.............................................................................. SECURE

Check the locking latch closed and directed aft.






13. Static Wicks.............................................. CHECK (THREE REQUIRED)

There should be one static wick on the wing trailing edge outboard of theaileron, and two on the trailing edge of the aileron. If an aileron static wickis missing, it should be replaced before the airplane is flown to ensureproper control surface balance.

14. Aileron, Flap, and Speed Brakes................. CONDITION AND SECURE

Ensure flap position matches indicator. Check the aileron for freedom andthe hinge points for security. Check the flap and speedbrakes for security.

15. Hydraulic Reservoir ....................................................................... CHECK

16. Air-Conditioning Exhaust, Lower Antennas, and Drains ..... CONDITIONAND CLEAR

Station E.Right Nacelle ............................................................................................. CHECK

1. Bleed-Air Precooler Inlet ............................................................... CLEAR

2. Engine Fluid Drain and TT2 Inlet .................................................. CLEAR

It is normal to find some residual fluid on the drain lines.

3. Generator Cooling Air Exhaust...................................................... CLEAR

4. Oil Filter Differential Pressure Indicator ...................... NOT EXTENDED

5. Oil Level ............ CHECK, FILLER CAP & ACCESS DOORSECURE

6. Engine Exhaust and Bypass Ducts ................ CONDITION AND CLEAR

Check for fuel leakage, damage to turbine blades, cracks, and generalsecurity.

7. Bleed-Air Precooler Exhaust Door .............................................. CLOSED

Do not push the door open. Cable damage may result.

CAUTION


8. Thrust Attenuator ........................................ CONDITION AND SECURE

The paddle should be firmly hydraulically stowed.

Station FEmpennage .................................................................................................. CHECK

1. Right Horizontal Stabilizer Deice Boot ................................ CONDITION

Check boots for cuts that might prevent inflation and for signs ofdelamination.

2. Right Horizontal Stabilizer, Elevator, and Trim Tab ............. CONDITION

Assure trim tab position matches elevator trim tab position indicator.

3. Rudder and Trim Tab ...................................... SECURE AND CORRECTSERVO TAB ACTION

4. Static Wicks (Rudder, Both Elevators, and Tailcone) ........ CHECK (NINEREQUIRED)

There should be three static wicks on the trailing edge of each elevator,two on the trailing edge of the rudder, and one on the tailcone. If a rudderor elevator static wick is missing, it should be replaced before flight inorder to ensure proper control surface balance.

5. Vortex Generators................................... CHECK (FIVE ON EACH SIDEOF THE VERTICAL STABILIZER)

6. Left Horizontal Stabilizer, Elevator, and Trim Tab ............... CONDITION

Ensure trim tab position matches the elevator trim tab position indicator.

7. Left Horizontal Stabilizer Deice Boot................................... CONDITION

Check boots for cuts that might prevent inflation and for signs ofdelamination.






Station GAft Compartment......................................................................................... CHECK

1. Fire Bottle Pressure Gages................................. CHECK PER PLACARD

Check that the pressure in the bottles is within limits for the ambienttemperature. A pressure/temperature chart is located between the bottles inthe tailcone compartment. Checking for correct bottle pressure is the onlyway to determine the bottles are full. The BOTTLE ARMED light on theglareshield will illuminate when the ENG FIRE switch is pushedregardless of bottle condition.

2. Junction Box Circuit Breakers ................................................................ IN(Check all visible circuit breakers.)

3. Equipment and Junction Box Access Doors ................................ SECURE

Check that the inner tailcone access door is closed and firmly latched.

4. Aft Compartment Baggage .......................................................... SECURE

5. Aft Compartment Light........................................................................ OFF

6. Aft Compartment Access Door ......................... SECURE AND LOCKED

7. External Power Service Door....................................................... SECURE

8. Battery Cooling Intake and Vent Lines .......................................... CLEAR

9. Lower Air Conditioning Compartment Vent(if installed) .................................................................................... CLEAR

Station HLeft Nacelle ................................................................................................. CHECK

1. Bleed-Air Precooler Intake............................................................. CLEAR

2. Bleed-Air Precooler Exhaust Door .............................................. CLOSED

Do not push the door open. Cable damage may result.

3. Engine Exhaust and Bypass Ducts ................ CONDITION AND CLEAR

Check for fuel leakage, damage to turbine blades, cracks, and generalsecurity.

CAUTION


4. Thrust Attenuator ........................................ CONDITION AND SECURE

The paddle should be firmly hydraulically stowed.

5. Engine Fluid Drains and TT2 Inlet................................................. CLEAR

It is normal to find some residual fluid on the drain lines.

6. Generator Cooling Air Exhaust...................................................... CLEAR

7. Oil Level ............ CHECK, FILLER CAP & ACCESS DOORSECURE

8. Oil Filter Differential Pressure Indicator ...................... NOT EXTENDED

Station ILeft Wing..................................................................................................... CHECK

1. Flap, Speedbrakes, Aileron, and Trim Tab.. CONDITION AND SECURE

Ensure flap position matches indicator. Check the aileron for freedom andthe hinge points for security. Check the flap and speedbrakes for security.

2. Static Wicks............................................. CHECK (THREE REQUIRED)There should be one static wick on the wing trailing edge outboard of theaileron and two on the trailing edge of the aileron. If an aileron static wickis missing, it should be replaced before the airplane is flown to ensureproper control surface balance.

3. Fuel Tank Vent................................................................................ CLEAR

If the vent is blocked, a negative pressure may build up in the wingcausing the tank to collapse.

4. Fuel Filler Cap.............................................................................. SECURE

Check the locking latch closed and directed aft.

5. Heated Leading Edge.......................... CONDITION, EXHAUST CLEAR

6. Stall Strip.....................CONDITION (NO NICKS OR DENTS), SECURE

7. Engine Air Inlet .............................................................................. CLEAR

8. Pylon Inlet ...................................................................................... CLEAR

9. Generator Cooling Air Inlet ........................................................... CLEAR






10. Engine Fan Duct and Fan .......................... CHECK FOR BENT BLADESNICKS, BLOCKAGE OF FAN

STATORS, AND FOREIGN OBJECTS

If the fan is windmilling, place hand on the bullet nose or install the enginecover to stop the rotation. If damage is observed, refer to the FJ44-1AEngine Maintenance Manual. (Remove cover if installed.)

11. Main Gear Door, Wheel, and Tire............... CONDITION AND SECURE

Check tire for wear and inflation to 98 5 psi and the door for security.Check wheel hubcap for condition and security of fastening. Check gearfor general security, fluid leakage, and an approximate oleo strut extensionof 2.5 inches if the airplane is fully fueled.

12. Fuel Quick Drains........ DRAIN AND CHECK FOR CONTAMINATION

Push straight up on the drains when taking fuel samples. The drain maylock open if it is turned.

13. Wing Leading-Edge Vent ............................................................... CLEAR

Station JFuselage Left Side....................................................................................... CHECK

1. Wing Inspection Light........................................................... CONDITION

2. Landing Light........................................................................ CONDITION

3. Cabin Door Seals (Primary and Secondary)................ CHECK FOR RIPSAND TEARS

CABIN INSPECTION1. Emergency Exit ............................................................................ SECURE

Check fit of door, handle stowed, and guard in place; handle lock pinremoved.

2. Passenger Seats.......................................... UPRIGHT AND OUTBOARD

Check that the exit doors are clear.

3. Door Entry Lights ................................................................................ OFF

The door entry light switch is located on the entry door post.

4. Lighted Exit Placards ................................................................... SECURE


COCKPIT INSPECTION 1. Oxygen Control Valve ............................................ CHECK IN NORMAL

2. Oxygen Masks .......................... CHECKED AND PROPERLY STOWED(CHECK MASK AND MICROPHONE)

Check masks at 100%, EMER and no blockages.

3. All Circuit Breakers ....................................................................... CHECK

4. Standby Gyro Switch ....................................... TEST (MOMENTARILY)/GREEN LIGHT ON

Check that the circuit breakers on both panels are in.

5. Standby Gyro ...................................... ON; CHECK AMBER LIGHT ON

6. Battery Switch ................................................................................... BATT

7. Battery Voltage ..................................... CHECK (24 VOLTS MINIMUM)Voltmeter checked at 24V for battery start; 29V with external powerapplied.

8. AVIONIC POWER Switch .................................................................... ON

9. ATIS/Clearance.................................................. CHECK (IF REQUIRED)

10. Rotary Test Switch............................. WARNING SYSTEMS CHECKEDPerform warning test with the rotary selector. Check in the OFF positionwith the red light extinguished.

11. Radar .................................................................................... OFF or STBY

12. Battery Switch ................................................... EMER (CHECK POWERTO EMERGENCY BUS ITEMS)

NOTEWith the battery switch in the EMER position, powershould be supplied to COMM 1, NAV 1, marker bea-con, overhead floodlights, pilot and copilot audiopanels, voltmeter, LH pitot static heater, standbygyro, pilot standby HSI, DG2, pilot altimeter, and en-gine N1 indicator.

COMM1/NAV 1 can be used on emergency bus forclearance/ATIS without operating other aircraft equip-ment if needed prior to start.







14. AVIONIC POWER Switch .................................................................. OFF

15. GeneratorsGEN (OFF if external power is to be used for start)16. FUEL BOOST Pumps ..................................................................... NORM

In the NORM position, the boost pumps will be automatically started andshut off during the engine start sequence.

17. Fuel Transfer ........................................................................................ OFF

18. LH GYRO Slave ............................................................................... AUTO

19. Parking Brake ....................................................................................... SETDepressing the brake pedals and pulling the parking brake handle out trapsapplied pressure to the wheel brakes. If the brake accumulator charge didnot indicate in the dark green or light green arc on the walkaround check,the accumulator must be charged by turning the battery switch to BATTshortly before setting the brakes.

20. WINDSHIELD BLEED AIR Manual Valves ...................................... OFF

21. Control Lock............... OFF (ENSURE THAT THE HANDLE IS FULLYIN AND CONTROLS AND THROTTLES ARE FREE)

Rotate the handle clockwise 45 from horizontal and push it in to release.With the control lock on, the throttles are held in the off detent. It ispossible however, to force a throttle past the lock which may requiredisassemably of the quadrant to restore normal operation of the controls.


23. Landing Gear Lights............. CHECK GREEN LIGHTS ILLUMINATEDAND UNLOCK LIGHT OUT

24. ANTISKID Switch ................................................................................ ON

25. Standby Gyro Caging Knob ......................... UNCAGED AND NO FLAG

26. Engine Instrument Warning Indicators .................................... NO FLAGS

27. Air Conditioner .................................................................................... OFF

28. AIR SOURCE SELECT Knob.......................................... AS REQUIREDPosition the TEMPERATURE SELECT control to the AUTO position inthe midrange.

NOTEBleed air enters the cabin hot (unconditioned) ifTEMPERATURE SELECT is set to MANUAL withthe AIR SOURCE SELECT in LH, RH, or BOTH.


29. RH GYRO....................................................................................... SLAVE

30. Throttles................................................................................. CHECK OFFEnsure both throttles are latched in the off position

31. Thrust Attenuator Switch.................................................................. AUTO

32. Engine Synchronizer ............................................................................ OFF

33. All Other Switches............................................................ OFF OR NORMSwitches OFF or NORM, generators GEN for battery start. All radios andavionics off to prevent the possibility of equipment damage due to voltagevariances during start.Because the engine bleed ports do not open until positive pressure isevident, it is not necessary to turn off the AIR SOURCE selector, and itmay be left in BOTH for starting and all normal operation.

34. External Power.................................... CONNECTED (IF APPLICABLE)

ITT may approach 1000C during battery starts athigher elevation airports. External power unit withat least 800 amp capacity is required for first enginestart at airports with elevation above 10,000 feet. Ifexternal power unit with variable shutoff current isused, it should be set to 1100 amps.

35. Battery and Standby Gyro Switches .......... OFF (IF THERE IS A DELAYBEFORE ENGINE START, OR

ON WITH EXTERNAL POWER UNIT)

NORMAL PROCEDURESThis chapter presents the abbreviated version of the expanded cockpit check-list provided with each CitationJet. Should any conflict exist between this in-formation and the checklist in the FAA approved Airplane Flight Manual, theflight manual shall take precedence. Any implied technique presented assumesthat proper pilot skill and judgment are exercised.QUICK TURNAROUNDWhen a complete preflight has already been accomplished and the conditionof the airplane has previously been thoroughly checked, it may be desirableto use the Quick Turnaround checklist in circumstances such as prior to suc-ceeding flights on the same day.

1. Standby Gyro ........................................................... ON/CHECK AMBER


CAUTION






3. Battery Voltage ..................................... CHECK (24 VOLTS MINIMUM)

4. External Power.................................... CONNECTED (IF APPLICABLE)

5. Generators ....................................... GEN (OFF IF EXTERNAL POWER)

6. AVIONIC POWER Switch .................................................................... ON

7. Rotary Test Switch................................ AOA (VERIFY SATISFACTORYPREFLIGHT TEST), THEN OFF

8. AVIONIC POWER Switch .................................................................. OFF

9. FUEL BOOST Pumps ..................................................................... NORM

10. All Other Switches............................................................ OFF OR NORM

11. Parking Brake ....................................................................................... SET

12. Control Lock ........................................................................................ OFF


14. Landing Gear Lights ...................................................................... CHECK

15. Standby Gyro Caging Knob ......................... UNCAGED AND NO FLAG

16. Engine Instrument Warning Indicators .................................... NO FLAGS

17. Throttles................................................................................. CHECK OFF

BEFORE STARTING ENGINES1. Preflight Inspection ................................................................ COMPLETE

2. Wheel Chocks .......................................................................... REMOVED

3. Cabin Door ................................................................ CLOSE AND LOCK

Check green indicators for proper door pin position, handle vertical and indetent.

4. Passenger Briefing.................................................................. COMPLETE

Include seat/seat belt adjustment, emergency exits, smoking, and oxygen.


5. Seats, Seat Belts, Shoulder Harnesses, and Rudder Pedals ..ADJUST ANDSECURE

Crew seats adjust fore and aft with the handle below the forward centerseat section, vertically with the handle on the aisle side forward corner,and tilt with the handle at the lower rear on the aisle side. Check seatslocked in the desired position. Check seat belts snug and shoulderharnesses latched to the buckle. Rudder pedals adjust individually bydepressing the tab on the inboard side and moving fore or aft. Threepositions are available. Check pedals locked in the desired position.

6. Fuel Quantity ............................................................................ CHECKED

7. Flashing Beacon Light........................................................................... ON


STARTING ENGINESClear the area behind the airplane and check for foreign objects in front ofthe engine inlets.

Due to hazards of foreign object ingestion and noise, the left engine shouldnot be running during boarding or deplaning. If last minute boarding is an-ticipated, the right engine should be started first.

NOTEIn crosswind conditions, starting the downwind en-gine first (for battery start) will produce a lower ITT.Otherwise either engine can be started first.

1. Flood and Center Panel Lights.....................FULL BRIGHT (FOR NIGHTOPERATIONS)

2. Start Button....................... PRESS MOMENTARILY; BUTTON LIGHTS

Momentarily depressing an ENGINE START button causes the button andengine instrument floodlights to illuminate, activates the fuel boost pumpand the associated FUEL BOOST ON annunciator light, and commencesthe engine rotation.

3. Throttles ......................................... IDLE AT 8% (N2) RPM (MINIMUM)AND WITH FAN (N1) RPM

Lower start ITT can be achieved by allowing N2 to peak (but not exceed12% N2) prior to advancing the throttle lever to idle.

For tailwind starts,ensure proper direction of fan rotation (N1 increasing)prior to bringing throttle to idle.






At a minimum of 8% turbine rpm, lifting the off latch and advancing thethrottle to start activates the ignition and the associated igniter light, andinitiates fuel flow.

4. ITT.................................................................................CHECK FOR RISE

Abort start if ITT rapidly approaches 1,000C or shows no rise within 10seconds. Do not exceed 975C for 7.5 seconds.

If engine maintenance has been performed, air in thefuel lines may cause a hot start. Ensure that properpurging procedures have been accomplished prior toattempting a start. Be prepared to abort the start.

5. Engine Instruments ...................................................... CHECK NORMAL

Check engine instruments within limits. Check that the starter hasdisengaged and that all annunciator lights are out except INVERTERFAIL, AOA HTR FAIL, P/S HTR OFF, AND ATTEN UNLOCK.

6. Fuel, Oil, Generator, and Hydraulic Annunciators ........ EXTINGUISHED

Check the FUEL LOW PRESS, FUEL BOOST ON, and FUEL LOWLEVEL lights extinguished. After light-off occurs, at approximately 45%turbine rpm, the starter relay opens, terminating ignition and fuel boost,and turns off the start button and the instrument floodlights. During abattery start with the GEN switch on, the generator will come on line,extinguishing the GEN OFF light at approximately 45% turbine rpm.

With external power in use, the GEN switches can be off until starting iscomplete. It may not be possible to bring the generators on line until theexternal power unit is removed. In any case, electrical equipment shouldnot be turned on until both GEN OFF lights are extinguished.

An overvoltage protection system protects the electrical system during useof an external power unit (EPU). The control unit monitors the externalpower unit voltage and will deenergize the external power relay if thevoltage is above 32.5 volts. External power cannot be reapplied until theelectrical power has been interrupted after a start termination byovervoltage protection, or until the voltage is reduced to below 32.5 volts.

Should automatic start sequencing not terminate, the boost pump, ignition,and associated lights will remain on. The starter however, will discontinuecranking due to speed sensing governed at approximately 45% N2 rpm.Depressing the STARTER DISENGAGE button will terminate theautomatic start sequence. This button is illuminated any time the PANELLIGHT CONTROL master switch is ON.

CAUTION


7. Other Engine..................................... START; REPEAT STEPS 2 THRU 6

If a generator cross start is to be accomplished, leave the throttle at idle N2rpm on the operating engine. The engine should idle at approximately56.2% N2 rpm (56.2 1.3% rpm). During generator cross starts, both startbuttons illuminate indicating that both start relays are closed.

8. External Power ................................ CHECK CLEAR (IF APPLICABLE)

9. Generators..... GEN (IF EXTERNAL POWER WAS USED FOR START)

It may not be possible to bring the generators on line until the externalpower is removed.

10. DC Amperes and Volts................................................................... CHECK

a. LH Generator ................................................................................. OFF

Check LH AMP drop, RH AMP INCR, voltage 29 0.25

b. RH Generator.................................................................................. OFF

Check RH AMP drop, Check voltage drop to battery voltage (24 voltsminimum).

c. LH Generator ................................................................................. GEN

Check on line (AMPS INCR, voltage 29 0.25)d. RH Generator ................................................................................. GEN

Check generators parallel and voltage 29 0.25.

e. Battery Switch................................................................................. OFF

Check LH AMP and RH AMP drop and voltmeter reads zero.

f. Battery Switch .............................................................................. BATT

Check voltage 29 0.25 volts

While the generator is off line, the MASTER CAUTION and theapplicable GEN OFF light will illuminate. If both generators are offline at the same time, the MASTER WARNING and both GEN OFFlights will flash.






BEFORE TAXIING1. Air Conditioner, Fans, Temperature Control..................... AS REQUIRED

NOTESelect both LH and RH positions, pause long enoughbetween selections to verify airflow from each po-sition. The selector should be positioned to BOTHafter checking the pressure sources, unless conditionsare such that FRESH AIR may be desired beforetakeoff.

The air-conditioner switch must be in AUTO or FAN,and the aft fan must be operating for the automaticcabin temperature control system to function.

2. Lights ................................................................................ AS REQUIRED

Turn on the interior and exterior lights as required, and adjust the interiorand instrument light intensity as desired.

NOTEBulb life is extended considerably by using the recog-nition/taxi light position for taxi.

3. Avionics Power Switch.......................................................................... ON

The right avionics switch serves as the master avionics power switch,supplying DC power to the avionics equipment requiring it, and to the leftON/OFF or NORM switch which controls the inverters.

4. AC Inverter Switch (SNs 0001 through 0099).................... CHECK INV 1AND INV 2 AND

SELECT INV 1 OR INV 2

5. Passenger Advisory Lights................................................. PASS SAFETY

6. Pressurization ................................................ AUTO/SET DESTINATION PRESSURE ALTITUDE +200 FEET

NOTETo obtain pressure altitude, add 100 feet to field el-evation for every 0.1 inch hg below 29.92 of baro-metric pressure. Subtract 100 feet for every 0.1 inchhg above 29.92.


NOTEWhen departing from airport elevations above 8,000feet, differences in pressure altitude and system tol-erances may cause the CAB ALT 10,000 FT annun-ciator and MASTER WARNING to illuminate.

7. Electric Elevator Trim .................................................. CHECK AND SET

Operate electric elevator trim nose up and push AP/TRIM DISC switch.Verify elevator trim wheel stops rotating. The trim should not operatewhile pressing only one side of the split switch. Repeat the check for nosedown trim. Repeat the check for the copilots AP/TRIM DISC switch. Setthe trim as required for center of gravity.

8. Flaps..... ........................................................................ CHECK AND SET

Set the flaps to ground flaps and verify that both speedbrakes deploy.Advance the throttles to above 85% N2 and verify that the speedbrakesretract and that the flaps >35 annunciator light illuminates. Retard thethrottles to idle and verify that the annunciator lights extinguish and thatthe speedbrakes redeploy. Set the flaps to TAKEOFF AND APPROACHand verify that the speedbrakes retract.

NOTEFor operations in extreme cold weather (below10C/14F), the flap system must be checked for fullextension to GROUND flaps and full retraction to UPprior to takeoff (until completion of SB 525-27-15).

9. Flight Controls...................................................... FREE AND CORRECT

Check for full travel of all controls. Observe the ailerons and elevator forcorrect movement. The ailerons and elevator can be seen from the cockpit.

10. Thrust Attenuators ............................................................. CHECK/AUTO

Place the thrust attenuator switch in stow; a white ATT STOWSELECTED advisory light will illuminate. Advance either throttle beyond85% N2 with the thrust attenuator switch in stow; the MASTERCAUTION light will illuminate. Bring the throttles to idle and place thethrust attenuators switch to TEST; The MASTER CAUTION light willilluminate. Place the thrust attenuator switch in AUTO with the throttles atidle; the thrust attenuators will deploy. Advance either throttle above idle; thethrust attenuators will stow then redeploy when the throttle is returned to idle.

SNs 0100 through 0359:

10 A. Inverter Switch........................................................ CHECK INVERTERS






Valid gyro information to pilot and copilot ADIs.

a. Select INV 1 and verify illumination of the INVERTER FAIL 2 lightand valid P and CP ADIs.

b. Select INV 2 and verify illumination of the INVERTER FAIL 1 lightand valid P and CP ADIs.

c. Select NORM and verify annunciator lights extinguish.

11. ATIS, Clearance, Flight Management System, Charts .................. CHECK

Check that the navigation radios are tuned to desired frequencies andcourses set. Check that the transponder is on the proper code and instandby, set to ALT just before takeoff.

12. Takeoff Data .......................................... CONFIRM FOR APPROPRIATETAKEOFF FLAP SETTING

Check field length required at takeoff gross weight against runwayavailable using actual temperature, runway slope, pressure altitude, andwind information. Check gross weight against maximum available takeoffweight using actual temperature and pressure altitude information. Referto performance tables for takeoff N1, V1, VR, V2, and best single engineclimb speed (VENR).


13. RH Attitude PULL-TO-CAGE Knob.................... PULL AND RELEASE

Check for no comparator monitor indication.


13 A. RH Attitude Indicator........................................................................ TEST

Press the ATT button and observe 30 right bank, 15 pitch, and fail flag.Release the button and observe straight and level indications and no flag.


14. Avionics........................................................................ CHECK AND SET

EFIS Test Button ............................................................................... PUSH

Pilot verify the following:

a. Radio altimeter test value on the pilots display is 50 feet (if installed).

b. Minimums aural or tone warning sound (if radar altimeter installed).

c. All digit readouts replaced with dashes (except radio altimeter).

d. All flags in view.

e. Command cue (if selected) bias from view.

f. Comparator monitor annunciates ATT and HDG.

g. TEST annunciated.

h. After five seconds, the text page appears showing each test functionstatus. As each function is tested, the FAIL annunciation will change toPASS.

TAXIINGGradually apply just enough thrust to break inertia. Reduce power to theamount necessary to achieve the desired taxi speed. Avoid riding the brakesand always place the throttles to idle before commencing braking. Cautionshould be exercised in congested areas to reduce the possibility of jet blastdamage to personnel and equipment.

Taxiing on one engine may be advisable at light weights to reduce brakewear, particularly in very cold weather when idle thrust is relatively high. Turn-ing capability into the operating engine is reduced however, and considera-tion should be given to the direction of anticipated turns in deciding whichengine to operate. Peak exhaust velocity to generate the necessary thrust willbe higher when using only one engine. Maneuvering in close quarters maydictate the use of both engines. If additional thrust should be needed for taxi-ing, place the thrust attenuator switch to the STOW position.

Ground operations in visible moisture with an outside ambient air tempera-ture from +10C or below require that engine anti-ice be ENG ON orWING/ENG.

1. Brakes ............................................................................................ CHECK






If, during taxiing, a hard brake pedal no braking con-dition is encountered, operate the emergency brakesystem. Maintenance is required before flight.

NOTEIf the antiskid is turned off prior to or during taxi-ing, it must be turned on prior to takeoff. The anti-skid must be turned on and the selftesting sequencecompleted (antiskid annunciator light out) while theairplane is stationary. If the airplane is taxiing whenthe antiskid system is turned on the antiskid test se-quence may not be completed successfully and theantiskid may not be operational during takeoff.

2. Flight Instruments .......................................................................... CHECK

Check the pilots EADI and EHSI have the desired functions selected anddisplayed. Check that the copilots ADI is erect and that no flag isshowing. Observe that the heading indicators, radio magnetic indicator(RMI), and magnetic compass are in agreement. Check the pilots GYROSLAVE in AUTO and the copilots in SLAVE, and that the vertical speedindicators (VSIs) are at zero.

3. Crew Briefing ......................................................................... COMPLETE

It is suggested that the pilot brief the copilot and crew on takeoffprocedures at this point. This briefing may consist of discussionconcerning crew coordination with respect to flap setting, use of anti-ice,review of takeoff power setting, V speeds and other call-outs desired,and normal and emergency procedures. A review of the planned departureand climb out procedures, as well as NAV aids to be used, may also beconducted at this time.

CAUTION


BEFORE TAKEOFF1. Anti-Ice/Deice Systems .........................................CHECK (WHEN ICING

CONDITIONS ARE ANTICIPATED)

Clearing the area behind the aircraft, set engine speed above 70% N2 rpmand turn on the engine and wing anti-ice and tail deice. Check forannunciators to illuminate and extinguish (approximately 1 minute). Turnthe wing and engine anti-ice off until ready to take off. Open thewindshield bleed air valves; turn on the windshield anti-ice; check flowand turn the anti-ice switches off and close the manual valves. Check forproper sequencing of the TAIL DEICE system. The TAIL DEICE (LH andRH) annunciators will illuminate, and remain illuminated only during theperiod of inflation of the automatic cycle. The left boot will inflate for sixseconds and deflate for 6 seconds, followed by six seconds of inflation ofthe right boot. Three minutes from the initial left boot inflation the cyclewill repeat, and continue repeating until the switch is turned off.

Do not operate windshield anti-ice on the ground athigh engine rpm.

Limit ground operation of pitot-static heat to twominutes to preclude damage to the pitot-static heaterand angle-of-attack probe.

Do not continue operating wing/eng anti-ice on theground at high engine rpm after the anti-ice annun-ciators have extinguished.

Do not operate deice boots when the ambient air tem-perature is below 35C (31F).

2. Passenger Seats ................ CHECK FULL UPRIGHT AND OUTBOARD

3. Cockpit Air Distribution Knob (AT Config) ..................... AS REQUIRED

AT configuration on aircraft -0047 and -0131 and subsequent, and aircraft-0001 through -0046 and -0048 through -0130 incorporating servicebulletin SB525-21-06, cockpit air distribution and windshield airdefogging has been improved by installation of a diverter valve that hascockpit air distribution knob on the tilt panel.

4. Air Source Selector........................................................................... BOTH

5. Flaps.......................................................................... SET FOR TAKEOFF

6. Trim........................................................................... SET FOR TAKEOFF

CAUTION







A LINE-UP CHECK is done prior to takeoff.

8. Ignition................................................................................................... ON

Turning the ignition ON will help to prevent a flameout if the engineshould ingest water spray or a foreign object on takeoff.

9. Pitot & Static Heat ................................................................................. ON

Limit ground operation of the pitot/static heat to two minutes to precludedamage to the pitot static tubes and the angle-of-attack probe.

10. Anti-ice/Deice Systems................................................ ON IF REQUIRED

11. Anti-Collision Lights ............................................................................. ON

NOTEDo not operate the anticollision lights in conditionsof fog, clouds, or haze as the reflection of the lightbeam can cause disorientation or vertigo.

12. Landing or Recognition Lights............................................. AS DESIRED

13. Transponder.......................................................................................... ALT

Set the transponder to the assigned mode and code.

14. Radar ................................................................................ AS REQUIRED

15. Annunciator Panel.......................................................................... CHECK

All annunciator lights should be extinguished with the possible exceptionof ENG or WING ANTI-ICE if either or both of these systems is selectedat a low power setting.

NOTEThe thrust ATTENUATOR UNLOCKED LH and RHannunciator lights will be illuminated with the throt-tles at idle but will extinguish when the throttles areadvanced for takeoff.


TAKEOFF1. Throttles ............................................................ SET TAKEOFF THRUST

Slowly and smoothly apply power while referencing the engineinstruments. A rolling takeoff may be used with sufficient runwayavailable, but it should be remembered that flight manual takeoff fieldlength data and N1 settings assume a static runup.

2. Engine Instruments ........................................................................ CHECK

3. Brakes ........................................................................................ RELEASE

Directional control is normally maintained with nose gear steering andrudder and upwind (wing down) aileron in crosswind conditions. For twocrewmember operations, it is suggested that the copilot perform the engineinstrument monitoring function and set the throttles enabling the pilot todirect his full attention to airplane control. N1 should be closely observed,and throttle corrections made as necessary to maintain takeoff thrust andensure symmetrical thrust application. Large differential power changes,particularly at the higher thrust settings, can induce yaw.

It is recommended that the copilot (for two crewmember operations)verbally state when takeoff thrust is set, cross-check the airspeedindicators at 70 knots and upon reaching V1 and VR. Positive backpressure is required to rotate the CitationJet and it should be accomplishedprecisely at VR. Early or late rotation may degrade takeoff performance.Rotation should be accomplished smoothly so that a decrease in airspeeddoes not occur. Normal rotation angle is 10 degrees nose up.

Should a serious irregularity become evident before reaching V1, thetakeoff should be aborted. With a problem after V1, the takeoff shouldnormally be continued. Procedures for abort and single engine takeoff areoutlined in the EMERGENCY section.






AFTER TAKEOFFCLIMB1. Landing Gear.......................................................................................... UP

When a positive rate of climb is indicated, pulling the gear handle out andmoving it to UP initiates the retraction cycle, illuminating the GEARUNLOCKED and HYD PRESS ON lights. Check that both lightsextinguish indicating the gear are up and locked.

2. Flaps ....................................................................................................... UP

At a comfortable altitude with wings level and a minimum airspeed of V2+10 KIAS, push the flap handle in (to clear the T.O. & APPR detent) andfull forward. Observe the position indicator to the left of the handle moveto FLAP UP. A small pitch change will occur. Minor retrimming will berequired as the airplane accelerates to climb airspeed.

3. Ignition ............................................................................................ NORM

When clear of any bird hazard and cockpit workload permits, return theIGNITION switches to NORM.

4. Climb Power......................................................................................... SET

Using indicated temperature and the RECOMMENDED MAXIMUMCONTINUOUS (CLIMB) thrust setting graph in Section IV of the FAAapproved Airplane Flight Manual, Section VII of this manual or theabbreviated checklist, determine climb N1. Fan N1 rpm will increase withaltitude and several throttle adjustments may be necessary during climb tomaintain the specified thrust setting.

During climb, observe the differential/pressure cabin altitude for correctcabin pressurization. The rate of cabin pressurization is automaticallycontrolled.

5. Engine Synchronizer (optional) ........................................ AS REQUIRED

When N1 is set within 2%, or N2 within 1% (left to right), turn the enginesynchronizer selector switch to FAN or TURB as desired. Cross-check theremaining engine instruments within limits.

6. Yaw Damper...................................................................... AS REQUIRED

With the yaw damper engaged, airplane control is improved and passengercomfort enhanced.

7. Passenger Advisory Lights................................................ AS REQUIRED


Placing the switch to SEAT BELT leaves that cabin advisory lightilluminated and extinguishes the NO SMOKING and emergency exitlights. If no turbulence is anticipated, placing the switch to OFFextinguishes both the advisory and emergency exit lights.

8. Anti-Ice/Deice Systems..................................................... AS REQUIREDUse of anti-ice reduces allowable fan speed and dictates close monitoringof interturbine temperature (ITT) and rpm limits.

9. Landing or Recognition Lights ............................................................ OFF

10. Pressurization................................................................................. CHECK

11. Oxygen Control Valve ............................ NORMAL (CABIN ALTITUDELOWER THAN 12,000 FT)

12. Altimeters .......................................................... SET TO 29.92 (1013 MB)AT TRANSITION ALTITUDE

AND CROSS-CHECK

NOTECrossfeed may not be possible above flight level 290.Fuel should be balanced prior to climbing aboveFL290 except for aircraft modified with the fueltransfer system (SNs 001-358 without SB 525-28-10).

CRUISE1. Cruise Power ........................................................................................ SET

Climb thrust is normally maintained upon level off until acceleration to thedesired cruise mode takes place. As the airplane accelerates and the ramair temperature (RAT) increases, N1 rpm may have to be adjusted to theappropriate setting. If the optional engine synchronizer is installed andengine rpm does not automatically synchronize at the desired cruisesetting, turn the engine synchronizer switch to OFF. This allows thesynchronizer actuator to center. Manually synchronize the engines byadjusting the throttles and turn the synchronizer switch to FAN or TURB.When operating at maximum range cruise, the thrust necessary to maintainoptimum angle-of-attack diminishes with fuel burn-off due to increasedperformance and lower airspeed requirements as weight decreases.

Although the airplane is not operationally restricted in rough air, flight insevere turbulence should be avoided. If severe turbulence is encountered, itis recommended that the igniters be turned ON and airspeed maintained atapproximately 180 KIAS. Maintain a constant altitude, avoid abrupt orlarge control inputs, and do not chase airspeed and altitude indications.

A comfortable cabin temperature is normally maintained with the AUTOTEMPERATURE SELECT in the twelve to two oclock position. During






daylight, the crew environment may not be an accurate reference to thecomfort level in the cabin due to solar heating taking place in the cockpitthrough the wide expanse of cockpit windows.

2. Anti-ice/Deice Systems..................................................... AS REQUIRED

Do not operate deice boots when indicated RAT isbelow 35C (31F).

The engine bleed-air anti-ice must be activated when operating in visiblemoisture at RAT temperatures of +10C or below and any time icing isoccurring. The pitot and static anti-ice is normally continuously operatedduring flight. Detailed instructions for operation of the engine anti-ice andsurface deice systems are found in Section II of this manual and in theFAA approved Airplane Flight Manual.

NOTECheck the deice system for proper operation prior toentering areas in which icing might be encountered.

3. Cockpit Air Distribution Knob (AT Config) ..................... AS REQUIREDAT configuration on aircraft -0047 and -0131 and subsequent, and aircraft-0001 through -0046 and -0048 through -0130 incorporating servicebulletin SB525-21-06, cockpit air distribution and windshield airdefogging has been improved by installation of a diverter valve that has acockpit air distribution knob on the tilt panel and flush floor grille on thefloor between pilot and copilot chairs.

DESCENT

1. Defog Systems .................................................................. AS REQUIRED

AT Configured:

a. Defog fanHI at start of descent

b. Cockpit air distribution knob ................................................ MAX

c. Windshield bleed-air manual valvesMAX and windshield bleed-air switchLOW below 18,000 feet if landing temperature/dewpoint spread is less than 10F (5C).

AS Configured:

a. Defog FanHI prior to descent

b. Windshield bleed-air manual valvesMAX and windshieldbleed-air switchLOW prior to descent if landing

CAUTION


temperature/dew point spread is less than 10F (5C).Warming the windshield with W/S BLEED air will assist in defrosting.

2. Pressurization ............................................................ SET DESTINATIONPRESSURE ALTITUDE +200

After beginning descent, verify destination pressure altitude +200 feet isset in the SET ALT field of the controller. Once the destination altimetersetting is known, in order to ascertain that the cabin pressure altitude forthe destination airport is correct, field pressure altitude can be determined.Because each 0.1 inch of mercury deviation from 29.92 equates to 100 feetdifference between field elevation and pressure altitude, an altimetersetting above standard yields a pressure altitude below field elevation andthe inverse is, of course, also true. As an example, descending to a fieldelevation of 350 feet with a reported altimeter setting of 29.77 wouldresult in a field pressure altitude of 500 feet. The cabin altitude shouldthen be set at 700 feet (500 + 200) feet to ensure depressurization prior totouchdown. Monitor the differential/cabin altitude in order to ensure thatthe cabin altitude descends at the correct rate to the lower altitude.

NOTEWhen departing from airport elevations above 8,000feet, differences in pressure altitude and system tol-erances may cause the CAB ALT 10,000 FT annun-ciator and MASTER WARNING to annunciate.

NOTETo obtain pressure altitude, add 100 feet to the fieldelevation for every 0.1 inch hg below 29.92 of baro-metric pressure. Subtract 100 feet for every 0.1 inchhg above 29.92.

3. Anti-ice/Deice Systems..................................................... AS REQUIRED

Engine anti-ice should be on and operating and W/S BLEED as requiredwhen operating in visible moisture at an outside air temperature from +10Cor below RAT.

4. Throttles ............................................................................ AS REQUIRED

Maintain sufficient power for engine anti-icing and tail deicing if systemsare operating. The engine anti-ice lights will remain OFF above 70% N2(minimum).

NOTEAt higher altitudes and lower outside air temperatures,higher N2 (73-78%) may be required to keep the an-nunciators extinguished and to operate the tail deiceboots if all anti-ice systems are operating.






5. Altimeters.......................................... SET AT TRANSITION ALTITUDEAND CROSS-CHECK

(TRANSITION ALTITUDE IS18,000 FT IN USA)

Set landing field barometric pressure in both altimeters when clearedbelow, or when passing transition altitude. Cross-check altimeters foragreement.

6. Landing Data (VAPP, VREF, N1, Landing Distance,Weight, and Factors).................................................................. CONFIRM

Refer to performance tables for VREF based on arrival gross weight. Checkrunway requirements based on gross weight and destination fieldinformation. Ascertain N1 and V2 for use in the event of a missedapproach.

7. Landing or Recognition Lights ......................................... AS REQUIRED

NOTEBulb life is extended considerably by using the recog-nition/taxi light position.

APPROACH1. Seats, Seat Belts, and Shoulder Harnesses................................... SECURE

Check seats locked in the desired position. Check seat belts snug andshoulder harnesses latched to the buckle.

2. Avionics and Flight Instruments .................................................... CHECK

Check NAV receivers on proper frequency and the required heading andcourse information set. Cross-check flight instruments for correctindications.

3. Radio Altimeter ...................................................... SET (IF INSTALLED)

Set decision height (DH) or minimum descent altitude on the EADI. ForVFR operation another desired altitude may be set to provide terrainproximity warning. Additional altitude selection (100 feet above DH, forinstance) may be set with the bug on a conventional radio altimeterindicator.

Decision height must be set in the EADI for Mini-mums or tone audio alert. Setting DH on the radaraltimeter will be set Minimums or tone audio alert.

WARNING





4. Passenger Advisory Switch................................................ PASS SAFETY

Turn on SEAT BELT/NO SMOKING signs and emergency exit lights.

5. Passenger Seats ................ CHECK FULL UPRIGHT AND OUTBOARD

6. Crew Briefing ......................................................................... COMPLETE

7. Fuel Crossfeed/Transfer ....................................................................... OFF

Check the CROSSFEED/TRANSFER knob OFF and the FUELCROSSFEED and FUEL BOOST ON annunciator lights extinguished.

8. Engine Synchronizer ............................................................................ OFF

The engine synchronizer should be OFF to prevent excessive wear withlarge or frequent throttle movements.


10. Antiskid ................................................................................... CHECK ON

11. Landing Lights....................................................................................... ON

12. Annunciator Panel.......................................................................... CHECK

13. Landing at airports above 10,000 feet:

a. Oxygen Control Valve..................................................... CREW ONLY

b. AIR SOURCE SELECT Knob ....................................................... OFF

NOTEObserve pertinent operational regulations for use ofsupplemental oxygen.

CAB ALT 10,000 FT annunciator and MASTERWARNING will illuminate as cabin altitude risesabove 10,000 feet pressure altitude.

Passenger oxygen masks will deploy automaticallyat cabin altitude of approximately 14,000 feet if oxy-gen control valve is left in the NORMAL position.

Failure to select pressurization source to OFF will re-sult in sudden cabin depressurization at touchdown.



14. Pressurization................................ CHECK (DESTINATION PRESSUREELEVATION +200 FEET SET)

15. Flaps ........................................................... TAKEOFF AND APPROACH

Flaps may be extended to T.O. and APPR below 200 KIAS. Checkindicator to verify position.

NOTEFor operations in extreme cold weather (below10C/14F), the flap system must be checked for fullretraction back to the UP position after selecting flapsTAKEOFF AND APPROACH. This check must becompleted prior to selecting flaps LAND (SNs 001359without SB525-27-15).Passing approximately 500 feet above ground level(AGL), check that the cabin pressurization indicatorshows zero differential pressure before landing. If thedifferential pressure is in excess of approximately 1/2psi, select a higher landing field elevation to ascendthe cabin. Any pressure existing at touchdown willbe dumped by the outflow valves (actuated by the leftmain gear squat switch) and may cause discomfort.

BEFORE LANDING

1. Ignition................................................................................................... ON

May preclude flameout should an engine problem arise or a bird strikeoccur during approach and landing phase.

2. Landing Gear........................................................ DOWN AND LOCKED

Pulling the gear handle out and moving it to DOWN illuminates the HYDPRESS ON and GEAR UNLOCKED lights while the gear is extending.Check three green flights on and the GEAR UNLOCKED and HYDPRESS ON lights extinguished. Maximum landing gear operating (VLO)and maximum landing gear extended (VLE) speed are both 186 KIAS.

3. Flaps ............................................................................................... LAND

The flaps may be extended to LAND below 161 KIAS. Flaps should be inthe LAND position for all normal landings. Check the indicator to verifyflap position. The flap handle must be pushed in to clear the T.O. andAPPR detent when LAND flaps are selected.

4. Pressurization ........................................ CHECK ZERO DIFFERENTIAL


5. Autopilot and Yaw Damper.................................................................. OFF

Turn the yaw damper to OFF to assure complete rudder authority to thepilot for landing. Utilize the AP/TRIM DISC button on either controlwheel or the YD ENGAGE button on the autopilot control panel.

6. Airspeed .............................................................................................. VREF

Consistently comfortable and safe landings are best achieved from astabilized approach. The point at which the airplane should be stabilizedwith an airspeed of VREF to VREF +10 knots, full flaps, and the desireddescent rate is normally coincident with commencing the final descent tolanding. Under instrument conditions, this usually occurs at the finalapproach fix inbound.

After passing the instrument approach fix outbound or nearing the airporttraffic area, airspeed should be reduced to below 200 KIAS and the flapsextended to the T. O. & APPR (15 degree) position. Approaching the finalinstrument fix inbound (one dot from glideslope intercept on an instrumentlanding system approach (ILS), or a downwind abeam position, extend thelanding gear. At the point where the final descent to landing is begun,extend the flaps to LAND, establish the desired vertical descent rate, andadjust the power to maintain VREF to VREF +10 KIAS.

Power management during the approach and landing phase is relativelyeasy in the CitationJet because an N1 setting in the 65-68 percent rangewill normally provide the desired indicated airspeed in variousconfigurations. Depending upon air traffic control requirements, thethrust necessary for the entire approach can often be set during thedescent. Keep in mind that the fan (N1) rpm will decrease slightly for afixed throttle setting with a decrease in altitude or indicated airspeed.Using a sea level airport with zero wind at a typical landing weight(8,500 pounds), a throttle setting that results in about 65 percent N1 willyield level flight indicated airspeeds of approximately 150 knots cleanand 130 knots with flaps T.O. and APPR. With the gear extended andflaps LAND, commencing an average descent (500 feet per minute) willresult in approximately VREF airspeed. Higher field elevations, landinggross weights, and/or a headwind component will require a higherpower setting.

For maneuvering prior to the final approach, minimum airspeeds of VREF+30, VREF +20, and VREF +10 should be maintained clean, flaps T.O. andAPPR, and flaps LAND respectively, to provide for adequate airspeedmargin above stall. While maneuvering prior to gear extension, maintainairspeed above 130 KIAS (copilots indicator) to avoid sounding thelanding gear warning horn.

Speed control on final should be precise for optimum land performanceand this is best accomplished by establishing VREF airspeed well beforecrossing the threshold. In gust wind conditions, it is recommended thatone half the gust factor in excess of five knots be added to VREF.






If landing above 12,000 feet pressure altitude, turn the OXYGENCONTROL VALVE to CREW ONLY and turn pressurization bleed airOFF to preclude passenger mask deployment.

7. Speedbrakes ............................................ RETRACT PRIOR TO 50 FEET

Extended speedbrakes are not approved for landing.

NOTEDo not allow turbine (N2) rpm to be less than ap-proximately 56%.

Approaching within approximately 50 feet of airport elevation, powershould be gradually reduced to idle. Wind velocity and direction willdictate the rate at which the throttles are retarded. In very high surfaceheadwind conditions, as an example, it may be necessary to maintain at ornear approach power until close to touchdown.

LANDING1. Throttles.............................................................................................. IDLE

Moving the throttles to IDLE extends thrust attenuators automatically aftertouchdown with the thrust attenuator switch in AUTO.

Touchdown, preceded by a slight flare, should occur on the main wheels.Check thrust at idle and lower the nose wheel.

Suggested crosswind technique involves flying a crab down final approachand aligning the longitudinal axis of the airplane to the runway centerlinewith rudder just before touchdown. The wide expanse of cockpit visibilitymakes small crab angles difficult to detect and particular attention shouldbe devoted to this area to achieve smooth crosswind landings.

2. Brakes .................................................. APPLY (AFTER TOUCHDOWN)

Braking should be commenced according to runway length available toreduce brake wear. Normally with excess runway, braking is begun afteraerodynamic deceleration to below 80 KIAS takes place. Apply smooth,gradually increasing pressure until a comfortable turn off speed is reached.For maximum braking performance, immediately after touchdown andwheel spin-up, apply continuous maximum effort to the brake pedals andhold to approximately 20 knots (do not modulate the brakes pedals). Asgroundspeed decays to approximately 20 knots, ease off the brake pedalpressure in order to avoid tire skidding when antiskid protection drops out.


If during landing, a hard brake pedal no braking con-dition is encountered, operate the emergency brakesystem. Maintenance will be required before nextflight.

NOTETo obtain maximum braking performance from theantiskid system, the pilot must apply continuousmaximum effort (no modulation) to the brake pedals.

NOTEDropout of the antiskid system occurs at approx-imately 12 knots where braking reverts to the powerbrake mode.

3. Flaps............................................................................... GROUND FLAPS

GROUND FLAPS extends flaps to 60 and extends speedbrakes.

Select GROUND FLAPS by lifting the flap handle and moving it to theextreme down position; the speedbrakes will be automatically selectedwhen the flap handle is placed in the GROUND FLAPS position and theflaps pass 38. The FLAPS > 35 annunciator light may illuminate if thesquat switch is not activated during the landing rollout.

The FLAPS >35 annunciator may illuminate and thrust attenuators maynot deploy if the nose is held up for aerodynamic braking.

CAUTION






ALL ENGINES GO-AROUND1. Throttles ............................................. SET FOR GO-AROUND THRUST

2. Airplane Pitch Attitude ...................................................... +10 DEGREES(USE FLIGHT DIRECTOR

GO-AROUND MODE)

3. Flaps ........................................................... TAKEOFF AND APPROACH

4. Climb Speed........................................................................................ VAPP

5. Landing Gear............................................... UP (WHEN POSITIVE RATEOF CLIMB IS ESTABLISHED)

6. Flaps ........................................................................................................ UP

7. Throttles .............................. SET MAXIMUM CONTINUOUS THRUST(MULTI-ENGINE)

AFTER LANDINGIt is recommended that the use of the checklist be delayed until the airplaneis clear of the runway.

1. Flaps ........................................................................................................ UP

Check that the HYD PRESS ON light extinguishes after the flaps are up.

Taxiing with the flaps in any position except up on a snow or slushcovered taxiway may result in obstruction of the flaps.

2. Ignition ........................................................................................ NORMAL

Place both ignition switches to NORM.

3. Pitot/Static Heat .................................................................................... OFF

4. Landing and Anti-Collision Lights .................................... AS REQUIRED

NOTEBulb life is extended considerably by using the recog-nition/taxi position for taxi.


5. Anti-ice/Deice/Defog Systems.......................................... AS REQUIRED

NOTEHigh humidity conditions may require the defog andwindshield bleed systems to remain on.

6. Transponder................................................................ OFF OR STANDBY

7. Radar ......................................................................... OFF OR STANDBY

SHUTDOWN1. Parking Brake ........................................... SET OR WHEELS CHOCKED

NOTEIf brakes are very hot, do not set the parking brake.

Heat transfer to the wheels and tires is increasedwith parking brakes set. This can cause the fusibleplugs to melt, deflating the tires. Do not leave the air-craft unattended without chocks unless the parkingbrake is set.

Always check the cabin differential pressure at zerobefore opening the door. Any pressure existing dueto malfunction of the left main gear squat switch orthe outflow valves could cause the door to open rapidlypresenting a hazard to personnel in the vicinity.

2. Defog Fan............................................................................................. OFF

DEFOG FAN switch to the center (OFF) position.


4. Flaps ......................................................... TAKEOFF AND APPROACH

Set the flaps to T.O. and APPR to facilitate the next preflight inspection. Ifthe airplane is to be unattended for a long period of time, or severeweather is expected, leave the flaps up.

5. Standby Gyro Switch ........................................................................... OFF

6. Standby Gyro .................................................................................... CAGE

7. Passenger Advisory Switch.................................................................. OFF






8. Exterior Lights ..................................................................................... OFF

Turn off the navigation lights.

9. Avionics Power and AC Inverter(SN 0001 through 0099) Switches ....................................................... OFF

10. Throttles ......................... OFF AFTER ALLOWING ITT TO STABILIZEAT MINIMUM VALUE FOR 2 MINUTES

Allow the ITT to stabilize at a minimum value for two minutes. This isusually accomplished during landing rollout and normal taxiing. Liftingthe latch and placing the throttles full aft terminates fuel flow to theengines.

Be sure that the first engine is correctly shutting down before shuttingdown the second engine.

11. Flashing Beacon Light ......................................................................... OFF

12. Battery Switch...................................................................................... OFF

BATT switch in the center (OFF) position. Care should be exercised that itis not placed in EMER. Emergency bus items (COMM 1, NAV 1, DG 2,flood lights and left pito