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Citation I/II/SII For training only 4H-1May 1998

Windshield Bleed Air Anti-Ice System(All Citations)

Ice

and

Rain

Pr

otection

W/S AIR

O'HEAT

TEMPERATURE

CONTROL

NOTE:SELECT LOW IFOAT IS ABOVE-18C.SELECT HIIF OAT IS-18COR BELOW.

AFT PRESSUREBULKHEAD

TEMPERATURETRANSMITTER

TEMPERATURE

WARNING

OVERHEATTEMPERATURETRANSMITTERS295F/146C

W/S BLEED AIRPOWER

FWD PRESSUREBULKHEAD

PRESSURESWITCH 5 PSI

TEMPERATURETRANSMITTER

RAM AIREXHAUST

AIRCONTROL

VALVEHEAT EXCHANGER

W/S BLEED AIR VALVE VALVERELAY

LH ENG BLEED AIR RH ENG BLEED AIR

OVERHEAT LIGHTW/ TEMP 295F/146C +ORPRESSURE LIGHTW/ SWITCH OFF AND5 PSI + IN LINE

TEMP/

PRESSURE

SWITCH

RELAY

LH MANUALW/S BLEED AIRCONTROL

RH MANUALW/S BLEED AIRCONTROL

RH WINDSHIELD NOZZLELH WINDSHIELD NOZZLE

SUPPLY

REGULATED AIR

RAM AIR

WARNLITE 2

W/S BLEED

LOW

O

F

F

HI

280F/138C

W/S AIR

O'HEAT

5A5A

260F/127C

RAM AIR IN

1

2

1

2

1

2

LH MAIN EXT BUS

(627 AND SUBSEQUENT)

RH CROSSOVER BUS

(SII & CII 02-626)

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4H-2 For training only Citation I/II/SIIMay 1998

Surface Deice SystemCitation; Citation I

23PSI

LH MAIN EXT BUS

CONTROLVALVE &

EJECTOR

PRESSURESWITCH

20 PSI

PRESSUREREGULATOR

PRESSURE SWITCH20 PSI

ENGINEBLEED

AIR

SURFACEDE-ICE

RESET

OFF

CONTROL VALVES

AND EJECTORS

ENGINE BLEED AIR

REGULATED BLEED AIR

VACUUM

PNEUMATIC AIR

OVERBOARD EXHAUST

SURF

DEICE

LH WING BOOT RH WING BOOT

LH HORIZ BOOT RH HORIZ BOOT

VERT

TAIL

BOOT

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Citation I/II/SII For training only 4H-3May 1998

Surface Deice SystemCitation II; CII-627

23PSI

LH WING BOOT RH WING BOOT

LH MAIN EXT BUS

CONTROL VALVEAND EJECTOR

PRESSURESWITCH

20 PSI

LH HORIZ BOOT RH HORIZ BOOT

VERTTAIL

BOOT

PRESSUREREGULATOR

PRESSURE SWITCH20 PSI

ENGINEBLEED

AIR

SURFACEDE-ICE

RESET

OFF

CONTROL VALVES

AND EJECTORS

ENGINE BLEED AIR

REGULATED BLEED AIR

VACUUM

PNEUMATIC AIR

OVERBOARD EXHAUST

SURF

DEICE

SURFACE

DEICE

Ice and Rain Protection

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Engine Anti-Ice System(except Citation SII)

4H-4 For training only Citation I/II/SIIMay 1998

CONTROLLER 130 TO 172 6F

NORM

O

F

F

LH

NORM

RH

IGNITION

ON

OFF

LH RH

ANTI-ICE

ENGINE

OFF

L ENG.

ICE FAIL

CURRENTSENSORS

5A

LH EXT BUS

155F165F

60F

CURRENTSENSOR

INPUT

TEMPSENSOR

INPUT

NORMAL CONTROL

LOW TEMP SWITCH (220F)

THROTTLESWITCH60% N2

STATOR BLEEDAIR VALVE

STATORVANES

COWL BLEED AIR VALVE

CONTROLRELAY

THERMOSWITCHES TEMPSENSOR

SPARE

ENG ICE

FAIL

LH RH

EXCITER

OVERHEATRELAY

ENGINE BLEED AIR

5A

RH CROSSOVER BUS

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Citation I/II/SII For training onlyJune 1997

TKS Anti-Ice SystemCitation SII

4H-5

GALANTI ICE

FLUID

01

3 57

WINGICE FAIL

TAILICE FAIL

ENGANTI ICE

ICE FLUIDPUMP FAIL

ICE FLDLOW

LH RH ENG SURICE FLDSYS ON

TAIL PROPORTIONING UNIT (SURFACE)

LEFT WINGPROPORTIONINGUNIT (SURFACE)

LEFT OUTBOARDWING PANELS

ENGINEPANELS

NUMBER 3SOLENOIDVALVE(AFT)

NUMBER 2 SOLENOIDVALVE (CENTER)

FILTER

FILTER

LOWLEVELSWITCH

MICRO-PROCESSOR

ENGINEPUMPENGINE

PANELS

RIGHT OUTBOARDWING PANELS

RIGHT WINGPROPORTIONING

UNIT (SURFACE)

PROPORTIONINGUNIT (ENGINE)

NUMBER 1SOLENOIDVALVE(FORWARD)

LEFTSTABILIZERPANELS

RIGHTSTABILIZERPANELS

SURFACE ENGINE PUMP

ENGINE PUMP FLOW

ALT ENG PUMP FLOW

ALT SURFACE PUMP FLOW

TKS FLUID

CUFF

FAIRING

CUFF

FAIRING

QUANTITYGAGE

1

2 3

4 1 2

34

4

3 2

1

SURFACEPUMP

4

1 2

3

FILTER

VENT LINE

FLUID TANK

SENSOR

PROBE

MICROPROCESSOR

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Engine Anti-Ice SystemCitation SII

4H-6 For training only Citation I/II/SIIJuly 1999

NORM

OFF

LH

NORM

RH

IGNITION

ON

LOW

LH RH

ANTI-ICE

ENGINE

LOW

5A

LH EXT BUS

LOW TEMP SWITCH (220 F)

THROTTLESWITCH60% N2

STATOR BLEEDAIR VALVE

STATORVANES

COWL BLEED AIR VALVE

ENGINEPANELS

PROPORTIONINGUNIT (ENGINE)

CUFF

FAIRING

CUFF

FAIRING

1 2

34

ENG

ANTI ICE

LH RH

ENGINE BLEED AIR

TKS FLUID

5A

RH CROSSOVER BUS

3A

SURFACE

O

F

F

R

E

S

E

T

ENG

ALL

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Citation I/II/SII For training only 4H-7June 1997

Ice and Rain ProtectionAnti-icing protection is provided for the:

I engine spinner, temperature probe, inlet lip, and stator vanesI inboard and outboard wing leading edgesI horizontal stabilizer leading edgesI vertical stabilizer leading edge (except SII)I windshieldI pitot tubes, static ports, angle-of-attack (AOA) probe, and

drain masts.

Ice DetectionOn the Citation SII, a detector and interpreter unit continuouslymonitors outside air conditions to provide a visual warning of icingconditions. The system operates on the principle that ice accu-mulation affects the thermal characteristics and resistance of the

systems probe. When icing accumulation occurs on the probe,the system illuminates the ICING DETECTED annunciator.

EngineDuring engine operation, hot bleed air flowing to the engine T1probes and bullet nose cone provides continuous anti-icing pro-tection. Placing the ENGINE ANTI ICE switches in ON, LOW, orHI (SII only) removes power from the inlet and stator vane anti-ice valves. The valves do not open until power is above 60% N2RPM and bleed air pressure reaches a minimum of 8 PSIG or 4PSIG (SII only). After the valves open, hot bleed air flows towarm the engine air inlet and stator vanes. When supplied witha 60 to 130 PSIG bleed air supply, the anti-ice valves regulatepressure to 14 to 18 PSIG or 11 to 14 PSIG (SII only). At powersettings below 60% N2 RPM, the valves close to prevent exces-

sive engine power loss.

With the ENGINE ANTI ICE switches ON or HI/LOW (SII only),the engine ignition system provides continuous ignition systemoperation and the inboard wing heating elements receive power(except SII).

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4H-8 For training only Citation I/II/SIIJune 1997

During engine anti-icing operation, the respective ENG ICEFAIL or ENGINE ANTI-ICE annunciator illuminates when:

I leading edge temperature is below 60F (16C)I heating element or circuit breaker opens

I overheat relay opens because of system malfunction oroverheat condition

I shorted or open temperature sensor

I stator valve not open with engine power below 60% N2 or

valve failureI engine inlet temperature below 170F (77C).

Surface Anti-Icing and DeicingOn the Citation, Citation I, and Citation II aircraft, turning theENGINE ANTI ICE switches ON supplies 28V DC to the inboardwing leading edge heating elements.

Turning the SURFACE DE-ICE switch on starts a 12 secondtimer that supplies low pressure bleed air to inflate the outboardwing, horizontal stabilizer, and vertical stabilizer deice boots. Asthe system cycles and supplies inflation pressure to the boots,two pressure switches illuminate the SURF DE-ICE annunciator.

On the Citation and Citation I, during the first six seconds theleft horizontal stabilizer and vertical stabilizer boots inflate andduring the last six seconds the wing and right horizontal stabiliz-er boots inflate. On the Citation II, during the first six secondsthe horizontal and vertical stabilizer boots inflate and during thelast six seconds the wing boots inflate.

When not inflated, 5.5 In Hg vacuum holds the deice boots tightagainst the leading edges.

On the Citation SII, a TKS fluid-based anti-icing system protectsthe wings and horizontal stabilizer from ice accumulation. Thesystem has two separate delivery subsystems that obtain fluidfrom common 7.5 gallon capacity reservoir. The engine subsys-tem delivers fluid to the cuff and fairing panels and the surface

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subsystem supplies the outboard wing and horizontal stabilizerleading edges. The ENG ANTI-ICE and SURFACE ANTI-ICE

switches control system operation (see Table 4H-1).With the system operating (ICE FLD SYS annunciator illuminat-ed), two electric pumps draw fluid from the reservoir and provideit under pressure to their respective systems through a filter,check valves, and solenoid valves to proportioning units for theengine, left and right wing, and tail. The proportioning unitsensure equal fluid delivery to the various panels. If pressure

drops to one of the delivery systems, pressure switches illumi-nate the associated ENG ANTI ICE, WING ICE FAIL, or TAIL ICEFAIL annunciator. If the pressure downstream of a pump drops,the associated ENG/SUR ICE FLUID PUMP FAIL annunciatorilluminates.

When reservoir fluid level drops and the low level switch actu-ates, the ICE FLD LOW annunciator illuminates to indicate

approximately 20 minutes of fluid left.


Citation I/II/SII For training only 4H-9July 1999

EngineSurface Results

LH RH

Table 4H-1; TKS Operation

LOW LOW ENG TKS to inboard leading edge,wing cuff, and fairing panelsat reduced rate (above22,000 ft); bleed air on.

HI HI ENG TKS to inboard leading edge,wing cuff, and fairing panelsat normal rate; bleed air on.

HI HI ALL TKS to inboard leading edge,wing cuff, fairing, and allother panels at normal rate;bleed air on.

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Windshield Anti-IcingSelecting LOW or HI on the W/S BLEED switch supplies power

to the windshield temperature controller. The controller thenremoves power to the windshield bleed air valve. The valveopens and bleed air flows through a heat exchanger before itreaches the manually operated shutoff valve. By regulating ramair flow through a heat exchanger, the system regulates bleedair temperature to approximately 127C (261F) with the W/SBLEED switch in the LOW position or 138C (280F) with the

switch in the HI position.With temperature data supplied by two sensors, the controlleropens the air control valve to increase ram air flow anddecrease bleed air temperature or closes the control valve toincrease ram air flow and decrease bleed air temperature. Ifbleed air temperature exceeds 146C (295F) or duct pressureexceeds 5 PSI with the bleed air valve closed, the W/S AIR

OHEAT annunciator illuminates.Rotating the WINDSHIELD BLEED AIR control knobs from theOFF position opens the manually operated shutoff valves toregulate windshield air flow.

With the WINDSHIELD BLEED AIR knobs in MAX and the W/SBLEED switch in LOW, pulling the PULL RAIN knob out opensaugmenter doors to change the windshield anti-icing system

airflow for rain removal.

An isopropyl alcohol-based fluid system supplements the bleedair windshield anti-icing system. Placing the W/S ALCOHOLswitch in ON supplies approximately 10 minutes of deicingalcohol to the pilots windshield.


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Pitot/Static Anti-IcingTurning the PITOT & STATIC switch on supplies 28V DC to the

pitot tube, static port, and angle-of-attack probe (if installed)heating elements. If a pitot tube or static port heating elementfails, current sensors illuminate the appropriate LH/RH P/SHTR OFF annunciator. The annunciators also illuminate if thePITOT & STATIC switch is in OFF. The AOA HTR FAIL annun-ciator illuminates if the AOA probe (if installed) heater fails.

In addition, heating elements in the water drain masts prevent

ice accumulation when electrical power is available.

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Surface Deice SystemCitation; Citation I; Citation II

Power Source Engine bleed airMain DC buses L/R

Distribution Wing boots L/RHorizontal stabilizer boots L/RVertical stabilizer boot

Control SURFACE DE-ICE switch

Monitor SURFACE DE-ICE annunciator (illuminatesin two 6-second cycles when SURFACEDE-ICE switch is activated)

Protection Circuit breakersSurface deice switch (reset)

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Engine Anti-Ice SystemCitation; Citation I; Citation II


Distribution Bleed air from each engine to:Engine inletFirst stage stator vanesNose cone, T1 probe

Engine ignitorsElectrically heated inboard wing leading edge

Control ENGINE anti-ice switches L/RThrottle microswitches: >60% N2

Monitor ENG ANTI-ICE FAIL L/R annunciatorsDC ammeters L/RStall strip WING INSP light

Engine ITT/RPMEngine ignition lights

Protection Circuit breakersBack up temp sensorsEngine inlet/stator fail safe valves

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Engine Anti-Ice SystemCitation SII


Distribution Bleed air from each engine to:Engine inletFirst stage stator vanesNose cone, T1 probe

Engine ignitorsTKS fluid manifolds to inboard wing fairing/cuff

Control ENGINE anti-ice switches L/RThrottle microswitches: >60% N2

Monitor AnnunciatorsENG ANTI-ICE FAIL L/RICE FLUID PUMP FAIL ENG/SUR

ICE FLD LOWICE FLD SYS ONICING DETECTED

Engine ITT/RPMIGNITION L/R lightsTKS quantity gage

Protection Circuit breakersProportioning valves

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Windshield Anti-Ice Systems


Distribution Windshield bleed nozzles L/RLeft side alcohol manifold

Control W/S BLEED AIR switchW/S Temperature controllerW/S ALC switchManual bleed air control valvesRain removal door handle

Monitor W/S AIR OHEAT annunciatorBleed air noise

Protection Circuit breakersWindshield bleed air valve fail safe

Overtemp transmitter

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TKS Surface Anti-Ice SystemCitation SII

Power Source RH Crossover bus (engine anti-ice)

Distribution WingWing fairing/cuffHorizontal stabilizer

Control SURFACE anti-ice switch

Monitor AnnunciatorsICE FLUID PUMP FAIL ENG/SURWING ICE FAILTAIL ICE FAILICE FLD LOWICE FLD SYS ONICING DETECTED

Windshield ice detection lightsTKS quantity gageDC ammeters L/R

Protection Circuit breakersCheck valvesSurface anti-ice warning

WARNING: The surface TKS system is not a deice sys-tem and does not remove significant accumulations of ice.When ice is detected, turn on the system immediately.If more than 1/8 inch of ice accumulates prior to systemactivation, leave the icing environment.

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NOTE: TKS fluid (monoethyleneglycol/isopropyl alcohol/deionized water solution) prevents ice accumulation.

However, TKS fluid may freeze if allowed to flow into dry,cold air.

NOTE: The TKS reservoir provides 1.5 to 7.5 hours ofanti-icing.

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4H-18 For training only Citation I/II/SIIJ 1997

Documents

12 ice rain