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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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Ice and Rain Protection
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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Ice and Rain Protection
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.
Ice and Rain Protection
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.
4H-10 For training only Citation I/II/SIIJune 1997
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Ice and Rain Protection
Citation I/II/SII For training only 4H-11June 1997
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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4H-12 For training only Citation I/II/SIIJune 1997
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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Ice and Rain Protection
Citation I/II/SII For training only 4H-13June 1997
Engine Anti-Ice SystemCitation; Citation I; Citation II
Power Source Engine bleed airMain DC buses L/R
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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4H-14 For training only Citation I/II/SIIJune 1997
Engine Anti-Ice SystemCitation SII
Power Source Engine bleed airMain DC buses L/R
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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Ice and Rain Protection
Citation I/II/SII For training only 4H-15June 1997
Windshield Anti-Ice Systems
Power Source Engine bleed airMain DC buses L/R
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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4H-16 For training only Citation I/II/SIIJune 1997
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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Ice and Rain Protection
Citation I/II/SII For training only 4H-17June 1997
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