ata 30 ice & rain protection

DIRECCIÓN DE MANTENIMIENTO E INGENIERÍA DEPARTAMENTO DE CONTROL DE CALIDAD CENTRO DE CAPACITACION MasAir

ICE & RAIN PROTECTION-B767 series

RVC MEX/ JUN 2003 ONLY TRAINING PURPOSE B767 Centro Capacitación Mas Air

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ICE & RAIN PROTECTION B 767 series



NOMBRE DEL PARTICIPANTE: NO. DE EMPLEADO: DEPARTAMENTO INSTRUCTOR: FECHA:


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THE INFORMATION CONTAINED IN THIS MANUAL HAS BEEN PREPARATED BY CENTRO DE CAPACITACION MasAir WITH INFORMATION EXTRACTED FROM AIRCRAFT MAINTENANCE MANUAL IN ORDER TO PROVIDE TECHNICAL TRAINING. AT MOMENT OF ELABORATION ITS CONSIDERED UPDATED, ALL TECHNICAL DATAS, LIMITS AND TOLERANCES USED ON THIS MANUAL AND SHOULD BE USED

ONLY FOR TRAINING PURPOSES

THE INFORMATION FOR FIELD JOBS MUST BE OBTAINED FROM CURRENT MANUALS.

LA INFORMACIÓN CONTENIDA EN ESTE MANUAL HA SIDO ELABORADA POR EL CENTRO DE CAPACITACIÓN MasAir, CON INFORMACIÓN EXTRAÍDA DE LOS MANUALES DE MANTENIMIENTO DE LA AERONAVE CON FINES DE INSTRUCCIÓN.

AL MOMENTO DE LA ELABORACIÓN DE ESTA INFORMACIÓN SE CONSIDERA ACTUALIZADA, CON LOS DATOS TÉCNICOS, TOLERANCIAS, LIMITES USADAS EN ESTE MANUAL QUE DEBE DE SER USADO:

SOLO CON FINES DE ENTRENAMIENTO

LA INFORMACIÓN PARA LOS TRABAJOS EN LA AERONAVE DEBERÁ DE SER OBTENIDO DE LOS MANUALES ACTUALIZADOS DE LA AERONAVE.

RVC MEX/ JUN 2003 ONLY TRAINING PURPOSE B767

Centro Capacitación Mas Air 3


ICE & RAIN PROTECTION-B767 series ATA 30-00 ICE & RAIN PROTECTION


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ICE & RAIN PROTECTION-B767 series ICE AND RAIN PROTECTION ICE PROTECTION THE ICE PROTECTION SYSTEMS PREVENT ICING ON CRITICAL AREAS ON THE AIRPLANE AND HELPS MAINTAIN AERODYNAMIC EFFICIENCY BY PROTECTING:

• WING LEADING EDGE SLATS • ENGINE NOSE COWLS • ENGINE PROBES (PT2/TT2) • PITOT STATIC PROBES • ANGLE OF ATTACK PROBES (AOA) • TOTAL AIR TEMPERATURE PROBE (TAT) • FLIGHT COMPARTMENT WINDOWS • WATER AND WASTE LINES

RAIN PROTECTION THE RAIN PROTECTION SYSTEMS INCREASE FORWARD VISIBILITY THROUGH USE OF:

• WINDSHIELD WIPERS • RAIN REPELLENT


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ICE & RAIN PROTECTION-B767 series ANTI-ICED AREAS WING THERMAL ANTI-ICING THREE OUTBOARD SLATS ON EACH WING ARE ANTI-ICED WITH ENGINE BLEED AIR. THE PILOT’S OVERHEAD (P5) CONTROL PANEL, WING THERMAL ANTI-ICE (TAI) VALVES, TEMPERATURE AND PRESSURE SWITCHES, VALVE LIGHTS AND EICAS ARE USED TO CONTROL AND MONITOR THE SYSTEM. THE SYSTEM CAN BE GROUND TESTED WITH A SWITCH ON THE P61 TEST PANEL. ENGINE NOSE COWL THERMAL ANTI-ICING THE LEADING EDGE OF THE ENGINE NOSE COWLS ARE ANTI-ICED WITH ENGINE BLEED AIR. EACH ENGINE ANTI-ICE VALVE IS CONTROLLED BY A SWITCH LIGHT ON THE P5 PANEL. ENGINE STATOR VANE ANTI-ICING IS ALSO ENABLED BY THIS SWITCH, A PRESSURE SWITCH IN EACH 5 SYSTEM, WHEN CLOSED, COMPLETES A CIRCUIT TO THE EICAS COMPUTERS. PROBE ANTI-ICING THE PITOT STATIC PROBES (TWO EACH SIDE ),ANGLE OF ATTACK PROBES (AOA) (ONE EACH SIDE), TOTAL AIR TEMPERATURE PROBE (TAT) (ONE ON LEFT SIDE) AND ENGINE PROBES ARE ELECTRICALLY HEATED. A SWITCH ON THE P61 TEST PANEL PROVIDES FOR TESTING OF ALL PROBES EXCEPT THE ENGINE PROBES. MALFUNCTIONS ILLUMINATE INDIVIDUAL LIGHTS ON THE MISCELLANEOUS ANNUNCIATOR PS PANEL AND PROVIDE AN INPUT TO THE EICAS COMPUTERS.


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RVC MEX/ JUN 2003 ONLY TRAINING PURPOSE Centro Capacitación Mas Air

B767

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ICE & RAIN PROTECTION-B767 series ANTI-ICED AREAS/RAIN PROTECTION FLIGHT COMPARTMENT WINDOW ANTI-ICING ALL FLIGHT COMPARTMENT WINDOWS ARE ELECTRICALLY HEATED USING TWO CONTROLLERS, EACH WITH BITE. THE CONTROLS FOR THE SYSTEM ARE ON THE PILOTS OVERHEAD P5 PANEL. A TEST SWITCH ON THE P61 PANEL PROVIDES FOR SYSTEM CHECKOUT. ENTRY/SERVICE DOOR WINDOW ANTI-FOGGING THE INNER PANE OF THE ENTRY/SERVICE DOORS’ WINDOW IS ELECTRICALLY HEATED. THE CONTROL FOR THE SYSTEM IS AUTOMATIC. WINDSHIELD WIPER SYSTEM THE TWO ELECTRICALLY OPERATED WINDSHIELD WIPERS ARE CONTROLLED FROM ONE SWITCH IN THE LOWER CENTER OF THE PS PANEL. RAIN REPELLENT SYSTEM THE RAIN REPELLENT SYSTEM SPRAYS LIQUID REPELLENT SOLUTION ON THE FORWARD WINDSHIELDS. THE INDIVIDUAL CONTROL SWITCHES ARE TOGETHER ON THE WINDSHIELD CONTROL PANEL OR THE LOWER CENTER OF THE P5 PANEL. WATER AND DRAIN LINE HEATERS INSULATION BLANKETS, TAPE HEATERS AND GASKET HEATERS ARE USED TO PREVENT FREEZING OF THE WATER SUPPLY LINES, DRAIN LINES, AND LAVATORY DRAIN FITTINGS IN AREAS SUSCEPTIBLE TO FREEZING. THERE ARE NO CONTROL SWITCHES FOR THE ABOVE HEATERS, THEY ARE ALL CONTROLLED AUTOMATICALLY.


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ICE & RAIN PROTECTION-B767 series PROBE ANTI-ICING PITOT STATIC PROBES THE FOUR PITOT STATIC PROBES (TWO EACH SIDE) ARE ELECTRICALLY HEATED. THEY ARE LOCATED SLIGHTLY BEHIND THE NO. 2 WINDOWS AT ABOUT FLOOR LEVEL. ANGLE OF ATTACK PROBES (AOA) THE TWO ANGLE OF ATTACK PROBES (AOA), LOCATED BETWEEN THE PITOT STATIC PROBES, HAVE AN ELECTRICALLY HEATED VANE AND CASING. TOTAL AIR TEMPERATURE PROBE THE TOTAL AIR TEMPERATURE PROBE, LOCATED ON THE LEFT SIDE SLIGHTLY BELOW AND JUST OUTBOARD OF THE NO. 1 WINDOW, IS ELECTRICALLY HEATED. BLEED AIR IS USED TO INDUCE AIRFLOW ACROSS AN INTERNAL SENSOR. ENGINE PROBES (PT2/TT2) THE ENGINE PROBE, LOCATED AT THE INSIDE TOP CENTER OF THE ENGINE NOSE COWL, IS ALSO ELECTRICALLY HEATED.


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ICE & RAIN PROTECTION-B767 series PIlOT-STATIC PROBE HEAT THE PITOT-STATIC PROBE HEAT SYSTEM PROVIDES ANTI-ICE FOR THE PROBES. SWITCHING RELAYS AUTOMATICALLY APPLY POWER TO THE PROBES UNDER THE PROPER CONDITIONS. THE CURRENT SENSING RELAYS INITIATE WARNINGS TO THE CREW IF A PROBE IS NOT RECEIVING HEAT WHILE THE AIRPLANE IS EITHER ON THE GROUND OR IN THE AIR.


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ICE & RAIN PROTECTION-B767 series PITOT-STATIC HEAT COMPONENT LOCATIONS PITOT-STATIC PROBES STA. 200, BOTH SIDES PROBE HEAT CIRCUIT BREAKERS OVERHEAD CIRCUIT BREAKER PANEL (P11) AND MAIN POWER DISTRIBUTION PANEL (P6). PROBE HEAT MONITOR LIGHTS ON ANNUNCIATOR PANEL ON PILOT’S OVERHEAD PANEL (P5). PROBE HEATER TEST SWITCH ON TEST PANEL ON P61. PROBE HEAT CONTROL AND MONITOR RELAYS THE FOLLOWING RELAYS ARE LOCATED IN THE FORWARD MISCELLANEOUS ELECTRIC EQUIPMENT PANEL (P33).

• CURRENT SENSING RELAYS (4) • AIR/GROUND RELAYS (4) • PROBE HEAT TEST RELAYS (2) • PROBE HEAT N2 RELAYS (2)

ENGINE SPEED CARDS (2) IN ELECTRICAL SYSTEMS CARD FILE (P50).


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ICE & RAIN PROTECTION-B767 series PITOT STATIC PROBE ANTI—ICING ELECTRICAL FUNCTIONAL DESCRIPTION THE PITOT STATIC PROBES ARE HEATED ELECTRICALLY USING TWO PHASE POWER (200V AC) IN THE AIR. ON THE GROUND WITH THE ENGINES OPERATING THEY ARE HEATED WITH SINGLE PHASE 11 5V AC. WHEN THE ENGINES ARE OFF, THE PROBES ARE NOT HEATED. WHEN CURRENT IS NOT SENSED BY THE CURRENT SENSING TRANSFORMER, AN ENGINE INDICATING AND CREW ALERTING (EICAS) ADVISORY MESSAGE IS DISPLAYED AND A LIGHT FOR THAT PROBE IS ILLUMINATED ON THE PILOTS OVERHEAD P5 PANEL. IF HIGH HEAT IS SENSED ON THE GROUND, AN EICAS MAINTENANCE MESSAGE IS RECORDED IN THE NON-VOLATILE MEMORY OF THE EICAS COMPUTER. THE TEST SWITCH ON THE P61, WHEN PLACED TO WINDOW/PROBE HEAT, TESTS THE SYSTEM IN HIGH HEAT AND THE PROBE LIGHTS ON THE MISCELLANEOUS ANNUNCIATOR PANEL P5 ARE EXTINGUISHED FOR THOSE PROBES THAT ARE OPERATIONAL. WHEN THE SWITCH IS RELEASED THE PROBE INDICATOR LIGHTS ILLUMINATE. CONTROL THE SYSTEM IS CONTROLLED AUTOMATICALLY THROUGH THE AIR/GROUND AND ENGINE N2 RELAYS.


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ICE & RAIN PROTECTION-B767 series ANGLE OF ATTACK PROBE HEAT (AOA) ELECTRICAL FUNCTIONAL DESCRIPTION THE PROBES ARE HEATED WITH 115 VOLTS AC POWER IN THE AIR AND ARE NOT HEATED ON THE GROUND UNTIL THE ENGINES ARE OPERATING. WHEN AN ANGLE OF ATTACK HEAT CURRENT SENSING RELAY FAILS TO SENSE CURRENT THROUGH THE VANE HEATER THE APPROPRIATE AOA ANNUNCIATOR LIGHT ON THE P5 PANEL IS ILLUMINATED AND THE ENGINE INDICATING AND CREW ALERTING (EICAS) DISPLAYS AN ADVISORY MESSAGE. A FAILURE OF THE CASE HEATER IS NOT ANNUNCIATED. ON THE GROUND THE SYSTEM IS TESTED BY PLACING THE TEST SWITCH TO THE WINDOW PROBE HEAT POSITION. THE LIGHTS ON THE P5 MISCELLANEOUS ANNUNCIATOR PANEL EXTINGUISH FOR THE OPERATIONAL PROBES AS CURRENT IS SENSED BY THE HEATER CURRENT SENSING TRANSFORMERS. WHEN THE SWITCH IS RELEASED THE LIGHTS ILLUMINATE. CONTROL THE SYSTEM IS AUTOMATICALLY CONTROLLED THROUGH THE AIR/GROUND AND ENGINE N2 RELAYS.


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ICE & RAIN PROTECTION-B767 series TOTAL AIR TEMPERATURE (TAT) PROBE HEAT

OPERATION/CONTROL SEQUENCE THE TAT PROBE HEAT IS CONTROLLED BY THE SYSTEM NO. 1 AIR/GROUND RELAY K514. THE INPUT TO THE TAT ANNUNCIATOR ON P5 AND TO EICAS IS CONTROLLED BY THE INDICATOR CIRCUIT CONSISTING OF THE TAT PROBE CURRENT SENSING RELAY K411, THE LEFT PROBE HEAT RELAY K644, AND THE SYSTEM NO. 2 AIR/GROUND RELAY, K51 7.

AIRPLANE AIRBORNE - HEAT ON THE HEATER CIRCUIT IS COMPLETED THROUGH RELAY K514’S UPPER CONTACTS. THE INDICATOR CIRCUIT IS OPEN (K411 UPPER CONTACTS AND K517 LOWER CONTACTS OPEN). BOTH THE TAT ANNUNCIATOR ON P5 AND THE LEVEL-C EICAS MESSAGE ARE OFF.

AIRPLANE AIRBORNE - HEAT OFF LOSS OF CURRENT THROUGH K411 CAUSES THE INDICATOR CIRCUIT TO BE COMPLETE THROUGH K411 AND K517 UPPER CONTACTS. BOTH THE TAT ANNUNCIATOR ON P5 AND THE APPROPRIATE LEVEL-C EICAS MESSAGE ARE DISPLAYED.

AIRPLANE ON GROUND - HEAT OFF ENGINES STOPPED: THE HEATER CIRCUIT IS OPEN THROUGH K514. THE INDICATOR CIRCUIT IS COMPLETE THROUGH K411 AND K644 UPPER CONTACTS AND K517 LOWER CONTACTS. BOTH THE TAT PROBE NO-HEAT ANNUNCIATOR ON P5 AND THE APPROPRIATE LEVEL-C EICAS MESSAGE ARE DISPLAYED.

ENGINES RUNNING: AS IN THE PREVIOUS CASE, THE HEATER CIRCUIT IS OPEN THROUGH K514. HOWEVER, K644 LOWER CONTACTS CLOSE THE INDICATOR CIRCUIT. CONSEQUENTLY, IN ORDER TO BE CONSISTENT WITH THE REST OF THE PROBE NO-HEAT INDICATIONS, BOTH THE TAT ANNUNCIATOR AND THE APPROPRIATE LEVEL-C EICAS MESSAGE ARE NOT DISPLAYED.

STATUS INPUT TO ADC THE OUTPUT OF A DEDICATED SET OF K411 CONTACTS TO THE LEFT AND THE RIGHT ADC MONITORS TAT HEATER ON, OR OFF, CONDITION.


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ICE & RAIN PROTECTION-B767 series ENGINE PROBE HEAT OPERATION THE SYSTEM IS AUTOMATICALLY CONTROLLED THROUGH THE AIR/GROUND AND ENGINE N2 RELAYS. THE ENGINE PROBE (PT2/TT2) PROTRUDES THROUGH THE FAN COWL ON THE UPPER SIDE OF EACH ENGINE; IT PROVIDES PRESSURE AND TEMPERATURE INFORMATION TO THE ELECTRONIC ENGINE CONTROL (EEC). 115 VOLTS AC IS USED TO POWER THE RESISTANT TYPE HEATER INSIDE THE PROBE IN THE AIR OR ON THE GROUND WITH THE ENGINE RUNNING. ON THE GROUND WITH THE ENGINE OFF THE PROBE IS NOT POWERED. WHEN THE PROBES CURRENT SENSING TRANSFORMER DOES NOT SENSE CURRENT THROUGH THE PROBE’S HEATER, THE ‘ENG EEC PROBES” LIGHT ON THE MISCELLANEOUS ANNUNCIATOR PANEL (P5) ILLUMINATES. NOTE THAT THE LEFT OR RIGHT ENGINE’S Pt2/Tt2 PROBE MAY CAUSE THE “ENG EEC PROBES” LIGHT. EICAS WILL PROVIDE A LATCHED STATUS AND MAINTENANCE LEVEL MESSAGES FOR THE APPROPRIATE PROBE WHEN THE ENGINE (S) ARE OPERATING OR DURING SPECIAL TEST CONDITIONS. THE SYSTEM IS TESTED ON THE GROUND BY PLACING TEST SWITCH SI, LOCATED ON THE P61, TO THE WINDOW/PROBE HEAT POSITION. IF BOTH PROBES DRAW POWER THEN THE ANNUNCIATOR LIGHT GOES OUT. WHEN THE SWITCH IS RELEASED, THE PROBES STOP DRAWING POWER AND THE LIGHT ILLUMINATES AGAIN.

WARNING: DO NO TOUCH PROBES DURING TEST. SEVERE BURNS MAY RESULT. CAUTION: DO NOT OPERATE PROBE HEATERS LONGER THAN 30 SECONDS MAXIMUM. WAIT FOR 5 MINUTES MINIMUM BETWEEN PROBE HEATERS OPERATION. PROBE DAMAGE MAY RESULT.

WHEN THE “ENG EEC PROBES” LIGHT DOES NOT GO OUT DURING THE WINDOW! PROBE HEAT TEST, THIS INDICATES THAT THE LEFT, RIGHT OR BOTH ENGINE PROBES MAY HAVE FAILED. TO DETERMINE WHICH PROBE HAS FAILED WITHOUT RUNNING ENGINES, THE FOLLOWING MAY BE DONE: APPLY POWER TO ALL BUSSES, ACTIVATE THE EEC GND TEST PWR SWITCHES (P61) TO THE ON POSITION FOR BOTH ENGINES, ACTIVATE THE CHANNEL 2 TEST SWITCHES ON BOTH N2 SPEED CARDS (P50), AND MONITOR THE STATUS PAGE OF EICAS FOR L (R) ENG PROBE HEAT MESSAGE (S).


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ICE & RAIN PROTECTION-B767 series PROBE HEAT TEST WINDOW/PROBE HEAT TEST THE WINDOW/PROBE HEAT TEST IS ACCOMPLISHED WITH ENGINES NOT OPERATING. OPERATING THE TEST SWITCH ON THE P61 TEST PANEL FORCES ALL THE PROBE HEATER CIRCUITS INTO THE AIR POSITION. ANY PROBE HEAT-OFF INDICATIONS ON THE ANNUNCIATOR PANEL (P5) AND ON THE UPPER EICAS DISPLAY UNIT SHOULD EXTINGUISH. ANY PROBE NOT DRAWING POWER DURING THE TEST WILL HAVE ITS ANNUNCIATOR ILLUMINATED. NOTE THAT ONE LIGHT “ENG EEC PROBES” IS USED THE LEFT AND RIGHT ENGINE Pt2/Tt2 PROBES.

WARNING: DO NOT TOUCH PROBES DURING TEST. SEVERE BURNS MAY RESULT.

CAUTION: DO NOT OPERATE PROBE HEATERS LONGER THAN 30 SECONDS MAXIMUM. WAIT FOR 5 MINUTES MINIMUM BETWEEN PROBE HEATERS OPERATION. PROBE DAMAGE MAY RESULT.

EICAS MESSAGES IF, DURING THE PROBE HEAT TEST, A PROBE HEATER CIRCUIT FAILS, EICAS WILL PROVIDE AN ADVISORY MESSAGE EXCEPT FOR ENGINE Pt2/Tt2 PROBES. ONE OF FOUR MESSAGE WILL BE DISPLAYED FOR THE PITOT-STATIC PROBES. CAPT PITOT, L AUX PITOT, F/O P1-TOT OR R AUX PITOT. IF A TAT PROBE HEATER CIRCUIT FAILS THEN THE MESSAGE TAT PROBE WILL BE DISPLAYED OR AS AN OPTION IF THE SYSTEM HAS TWO TAT PROBES THE MESSAGE WILL BE L TAT PROBE OR R TAT PROBE. IF AN AOA PROBE HEATER CIRCUIT FAILS THEN THE MESSAGE WILL BE L AOA PROBE OR A AOA PROBE. IF TWO OR MORE OF ANY OF THE PROBES ARE NOT OPERATING EXCEPT FOR ENGINE Pt2/Tt2 PROBES, THE INDIVIDUAL MESSAGE WILL BE REPLACED WITH PROBE HEAT. EICAS HAS DEDICATED LATCHED STATUS AND MAINTENANCE MESSAGE FOR FAULTY ENGINE Pt2/Tt2 PROBES. EICAS CAN ONLY ACTIVATE THE APPROPRIATE MESSAGE WHEN IT SENSES THE ENGINE RUNNING CONDITION AND A FAULTY PROBE HEATER SIGNAL FROM THE APPROPRIATE ENGINE ELECTRONIC CONTROL (EEC).


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ICE & RAIN PROTECTION-B767 series PROBE HEAT EICAS INDICATIONS FUNCTIONAL DESCRIPTION WHEN ANY ONE OF THE ELECTRICALLY HEATED PROBE CURRENT SENSING TRANSFORMER FAILS TO DETECT CURRENT TO A PROBE, A GROUND IS PROVIDED THROUGH A RELAY ASSOCIATED WITH THAT TRANSFORMER. THE RELAY TURNS ON AN INDIVIDUAL AMBER LIGHT ON THE P-5 MISCELLANEOUS ANNUNCIATOR PANEL FOR EACH AFFECTED PROBE AND SENDS A FAILURE SIGNAL TO THE EICAS COMPUTERS. IF THE EICAS COMPUTER RECEIVES ONLY ONE FAILURE INPUT, THAT PROBE IS IDENTIFIED BY A MESSAGE ON THE CRT. IF MORE THAN ONE INPUT SIGNAL IS RECEIVED BY THE COMPUTERS, A SINGLE MESSAGE, PROBE HEAT, IS DISPLAYED. ALL PROBE HEAT EICAS ALERT MESSAGES ARE CLASS C ADVISORY.


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ICE & RAIN PROTECTION-B767 series WINDOW HEAT CONTROL UNIT WINDOW HEAT IS PROVIDED THROUGH TWO CONTROLLERS WITH BITE IN EACH UNIT. EACH CONTROL UNIT HAS THREE CHANNELS. ONE CHANNEL CONTROLS WINDOW NUMBER ONE, AND THE REMAINING TWO CHANNELS CONTROL OPPOSITE 2 AND 3 SIDE WINDOWS. THE CONTROLLERS ARE LOCATED IN THE MAIN EQUIPMENT CENTER E2-1 SHELF (NO. 2) AND E1-2 SHELF (NO. 1). BUILT-IN-TEST (BIT) MONITORS THE OPERATION OF AND RECORDS FAULTS IN THE WINDOW HEATERS, TEMPERATURE SENSORS, AND THE CONTROL UNIT. THE TEMPERATURE SENSORS ARE LAMINATED INTO THE WINDOWS. A SPARE SENSOR IS PROVIDED FOR EACH WINDOW. THE NO. 2 WINDOW USE A COILED EXTENSION CORD FOR POWER AND SENSING LEADS AND ALLOWS THE WINDOW TO BE OPENED AND CLOSED.


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ICE & RAIN PROTECTION-B767 series WINDOW HEAT CONTROL AND INDICATION POWER POWER FOR THE LEFT FORWARD AND RIGHT SIDE WINDOW HEAT CONTROL UNIT COMES FROM THE LEFT MAIN BUSSES. THE NUMBER 1 WINDOW USES 2-PHASE, 115 VOLT AC POWER TO MAINTAIN A REGULATED 95 DEGREES F (35 DEGREES C). NUMBER 2 AND 3 WINDOWS USE SINGLE-PHASE AC POWER FROM A SEPARATE CIRCUIT. THESE WINDOWS USE A CYCLING FULL ON AND OFF CIRCUIT TO MAINTAIN 100 DEGREES F TO 105 DEGREES F (37.8 DEGREES C TO 40.6 DEGREES C). OVERHEAT FOR ANY OF THE WINDOWS IS ANNUNCIATED AT 110 DEGREES F (43.3 DEGREES C). WINDOW NUMBER 1 WINDOW NUMBER 1 USES THE 2-PHASE POWER TO GENERATE A SAW TOOTH CARRIER WAVE. AT THE SAME TIME, THE WINDOW SENSOR RESISTANCE IS MEASURED, AND IF THERE IS A TEMPERATURE ERROR, A HEAT COMMAND IS GENERATED. THIS HEAT COMMAND IS PHASED SLOWLY ON INITIAL POWER UP DUE TO A SIX-MINUTE RAMP GENERATOR. THE HEAT COMMAND IS SUPERIMPOSED ON THE SAW TOOTH GENERATOR WAVE. THIS CLIPS THE SIGNAL INTO A SERIES OF ON AND OF F COMMANDS. THESE COMMANDS ARE USED BY THE SILICON CONTROLLED RECTIFIER TO PASS AC POWER TO THE WINDOW. WINDOWS 2 AND 3 WINDOWS 2 AND 3 USE A DIFFERENT SCHEME TO REGULATE TEMPERATURE. THE SENSOR IN THE WINDOW WILL SWITCH ON THE FULL SINGLE-PHASE AC POWER AT 100 DEGREES F AND TURN THE POWER OFF AT 105 DEGREES F. UNDER NORMAL IN-FLIGHT CONDITIONS, THIS WOULD ROUGHLY APPROXIMATE ONE MINUTE ON, ONE MINUTE OFF. THE SYNCH PULSE GENERATOR TIMES THE ZERO VOLTS CROSSING POINT OF THE SINE WAVE SO THAT THE RECTIFIER CIRCUITS PASS THE ENTIRE AC CURRENT. OPTO-ISOLATORS ARE LIGHT SENSOR CIRCUITS USED PRIMARILY FOR VOLTAGE AND NOISE ISOLATION DURING SIGNAL TRANSFER.


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ICE & RAIN PROTECTION-B767 series BITE ALL THREE WINDOW CHANNELS HAVE TAPS INTO THE BITE CIRCUIT. THESE TAPS ME SURE POWER ON, SENSOR RESISTANCE, OUTPUT CURRENT, AND ASYMMETRY. USING LOG 1 C IN THE BITE CIRCUITRY AND THE MENTIONED INPUTS, IT IS POSSIBLE TO DETERMINE CONTROL UNIT, WINDOW, OR SENSOR FAULTS. THE INOP LIGHT CAN COME ON FOR: ASYMMETRICAL OUTPUT, SHORTED SENSOR, OPEN SENSOR, OVERHEAT (110 DEGREES F), DEMAND WITHOUT HEAT, HEAT WITHOUT DEMAND, CONTROL SWITCH OFF AND INPUT POWER NOT PRESENT. A BITE CHECK CAN BE INITIATED EITHER AT THE CONTROL UNIT, OR ON THE P61 PANEL. VARIOUS TIME DELAYS IN THE CIRCUIT HELP TO REMOVE SPURIOUS FAULTS. ANY FAULTS DISCOVERED REMOVE POWER FROM THE ASSOCIATED MOP RELAY(S). EICAS THE EICAS COMPUTERS HAVE THE CAPABILITY OF DISPLAYING MESSAGES RELATING TO THE INDIVIDUAL LIGHTS TO THE P5 CONTROL SWITCHES, OR IF MORE THAN ONE INOP LIGHT IS ON AT THE SAME TIME, THE EICAS COMPUTER DISPLAYS THE GENERIC MESSAGE “WINDOW HEAT”.


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ICE & RAIN PROTECTION-B767 series ENTRY/SERVICE DOOR WINDOW HEATING PURPOSE THE HEATING SYSTEM FOR THE ENTRY/SERVICE DOOR MOUNTED WINDOW IS DESIGNED TO PREVENT FOGGING OF THE WINDOW. LOCATION THE ELECTRICALLY HEATED INNER PANE IS MOUNTED ON THE INBOARD SIDE OF THE WINDOW’S PRISM. PHYSICAL DESCRIPTION/FEATURES THE INNER PANE ASSEMBLY CONSISTS OF TEMPERED WINDOW GLASS, ELECTRICAL GRID HEATING ELEMENT, AND AN INTEGRALLY BONDED SILICON BORDER SEAL. THE INNER PANE ASSEMBLY IS SECURED TO THE PRISM BY A PLASTIC RETAINING RING. THE RING IS SECURED BY THREE OF THE FOUR WINDOW CLAMPS. THE HEATING ELEMENT IS ELECTRICALLY CONNECTED BY DOOR MOUNTED WIRING THROUGH A QUICK-DISCONNECT ON THE UPPER PART OF THE DOOR TO CEILING AND FUSELAGE WIRING. OPERATION WINDOW HEATING IS AUTOMATIC AND IS ACTIVATED ANY TIME POWER IS ON THE RIGHT 28 VOLT DC BUS


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ICE & RAIN PROTECTION-B767 series WINDSHIELD WIPER WINDSHIELD WIPER/CONVERTER TWO WINDSHIELD WIPER ASSEMBLIES ARE USED TO ASSIST IN MOISTURE REMOVAL FROM THE NO. 1 LEFT AND RIGHT. WINDSHIELDS. EACH MOTOR/CONVERTER ASSEMBLY IS REMOVED/INSTALLED EXTERNALLY WITH AN ACCESS PANEL TO WHICH IT IS FASTENED. WINDSHIELD WIPER ARM THE WINDSHIELD WIPER ARM SUPPORTS THE BLADE, THE PRESSURE ADJUSTMENT BOLT ADJUSTS THE FORCE OF THE WIPER BLADE ON THE WINDSHIELD. TURNING THE BOLT CLOCKWISE INCREASES PRESSURE. NOMINAL BLADE PRESSURE ON THE WINDSCREEN IS 15 POUNDS. ARM POSITION SCREWS ALLOW ARM ADJUSTMENT TO POSITION THE WIPER BLADE ON THE WINDSHIELD. WINDSHIELD WIPER BLADE THE 27” WIPER BLADES ARE BOLTED TO THE WIPER ARMS. A PLUNGER MECHANISM WITH AN ANGLED LEVER HOLDS THE BLADE IN THE PROPER OPERATING ANGLE ON THE WINDSHIELD AND ALIGNS IT IN THE PARKED POSITION WHEN THE SYSTEM IS TURNED OFF. A LIFT BLOCK ASSEMBLY HOLDS THE WIPER BLADE AWAY FROM THE WINDSHIELD IN THE PARKED POSITION AND CAUSES THE ANGLED LEVER AND PLUNGER MECHANISM TO ALIGN THE BLADE.

CAUTION: DO NOT ALLOW WIPER BLADE TO MOVE ON A DRY WINDSHIELD.


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ICE & RAIN PROTECTION-B767 series WINDSHIELD WIPER SCHEMATIC ELECTRIC FUNCTIONAL DESCRIPTION A THREE POSITION ROTARY SWITCH (HIGH, LOW, OFF) LOCATED ON THE BOTTOM CENTER OF THE PILOT’S OVERHEAD PANEL (P5) CONNECTS 28 VOLT DC POWER TO GROUND. POWER THROUGH THE SWITCH COMES FROM BOTH BUSES (LEFT AND RIGHT 28 VOLT DC). IN THE FOLLOWING POSITIONS, THE SYSTEM OPERATES AS DESCRIBED: HIGH -POWER IS SENT THROUGH THE MOTOR WINDING CIRCUIT IN PARALLEL. THE MOTOR OSCILLATES THE WIPER AT 260 +/- 40 STROKES PER MINUTE. LOW -POWER IS SENT THROUGH THE MOTOR WINDING IN SERIES. THE WIPER OSCILLATES AT 180 +/- 45 STROKES PER MINUTE. OFF -THE CIRCUIT IS REVERSED THROUGH A CAM OPERATED SWITCH WHICH CONNECTS POWER 26 VOLT DC TO THE MOTOR ARMATURE. WHEN THE BLADE IS IN THE PARKED POSITION THE MOTOR CAM OPENS THE SWITCH AND DEACTIVATES THE CIRCUIT. CONTROL THE CAPTAINS AND FIRST OFFICER WINDSHIELD WIPERS ARE CONTROLLED FROM THE SAME SWITCH. WAFERS WITHIN THE SWITCH PROVIDED CONTACT FOR THE VARIOUS CIRCUITS OPERATING THE SYSTEM.


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ICE & RAIN PROTECTION-B767 series RAIN REPELLENT ASSEMBLY (SYSTEM DELETED) RAIN REPELLENT BOTTLE AND SHUTOFF ASSEMBLY A DISPOSABLE PRESSURIZED BOTTLE (40 TO 80 PSI), CONTAINING RAIN REPELLENT FLUID, SCREWS INTO AN ADAPTOR. THE ADAPTOR OPENS THE SUPPLY VALVE IN THE BOTTLE. A RETAINER CLAMP HOLDS THE BOTTLE IN THE ASSEMBLY. A SHUTOFF VALVE BELOW THE ADAPTOR IS NORMALLY OPEN AND IS CLOSED ONLY FOR BOTTLE REPLACEMENT. A FLOAT TYPE VISUAL FLUID LEVEL RESERVOIR, DIRECTLY BELOW THE SHUTOFF VALVE, ALLOWS A VISUAL INDICATION OF NEED FOR BOTTLE REPLACEMENT. THE PRESSURE GAGE BELOW THE VISUAL INDICATOR INDICATES SYSTEM PRESSURE. THE ENTIRE ASSEMBLY IS LOCATED ON THE BULKHEAD BEHIND THE FIRST OBSERVER’S STATION. SOLENOID VALVES AND ACCUMULATOR TWO SOLENOID OPERATED VALVES AND AN ACCUMULATOR ARE LOCATED BEHIND THE PILOT’S (P2) PANEL. THE VALVES DISPENSE REPELLENT FLUID TO THE NO. 1 LEFT AND RIGHT WINDSHIELDS. THE VALVES ARE OPERATED FROM INDIVIDUAL SWITCHES ON THE PILOTS’ OVERHEAD (P5) PANEL. THE ACCUMULATOR ASSISTS IN PURGING THE NOZZLES OF FLUID WITH BLEED AIR. SPRAY NOZZLES TWO SPRAY NOZZLES, ONE BELOW EACH WINDSHIELD, (NO. 1 L & R) SPRAY REPELLENT FLUID ON THE WINDSHIELD. THE LEFT SOLENOID VALVE AND SPRAY NOZZLE ARE NOT SHOWN IN THE EXPANDED VIEW.


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ICE & RAIN PROTECTION-B767 series RAIN REPELLENT SYSTEM FUNCTIONAL DESCRIPTION RAIN REPELLENT FROM THE PRESSURIZED BOTTLE IS AVAILABLE TO THE SYSTEM WHEN IT IS SCREWED INTO THE ADAPTOR TO OPEN THE VALVE IN THE BOTTLE. OPENING THE SHUTOFF VALVE BELOW THE BOTTLE WILL PRESSURIZE THE SYSTEM FROM THE BOTTLE AND FORCE THE FLUID INTO THE VISUAL RESERVOIR AND THE SUPPLY LINE UP TO THE SOLENOID VALVES. WHEN THE BOTTLE IS REMOVED, ITS VALVE RESEATS. THE FLOAT INDICATOR SHOWS ONLY WHEN FLUID LEVEL IS DEPLETED ENOUGH FOR BOTTLE REPLACEMENT. THE PRESSURE GAUGE INDICATES SYSTEM PRESSURE FROM THE BOTTLE. AT 20 PSI THE POINTER ENTERS A YELLOW BAND LABELED “REPLACE”.

NOTE: THE VISUAL FLOAT INDICATOR MAY OR MAY NOT SHOW LOW FLUID AT THIS TIME. THE SHUTOFF VALVE, BELOW THE ADAPTOR, WHEN TURNED OFF FOR BOTTLE REPLACEMENT, PREVENTS REPELLENT FROM BEING BLOWN BACK OUT OF THE LINE WHEN THE BOTTLE IS CHANGED. BLEED AIR FROM THE PNEUMATIC MANIFOLD, GOING THROUGH THE ACCUMULATOR, PURGES REPELLENT FROM THE NOZZLES PREVENTING CLOGGING. THE INDIVIDUALLY CONTROLLED SOLENOID VALVES ALLOW REPELLENT TO BE SPRAYED ON EITHER OF THE NO. 1 WINDSHIELDS. CONTROL A PUSHBUTTON SWITCH TO THE LEFT OF THE WINDSHIELD WIPER SWITCH, (ONE FOR EACH NO. 1 WINDSHIELD), WHEN PUSHED, COMPLETES A CIRCUIT TO THE SOLENOID VALVE. A TIME DELAY IN THE CIRCUIT ALLOWS THE SOLENOID VALVE TO BE OPENED FOR 400 MILLISECONDS, AND THEN CLOSES IT, STOPPING FLOW.


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ICE & RAIN PROTECTION-B767 series RAIN REPELLENT BOTTLE SERVICING THE BOTTLE IS TO BE REPLACED WHEN THE FLOAT IN THE RESERVOIR ALIGNS WITH THE REPLACEMENT MARK ON THE SIGHT LEVEL, OR WHEN THE PRESSURE GAUGE (BELOW THE RESERVOIR) DOES NOT READ IN THE GREEN BAND. REMOVE/INSTALL CLOSE MANUAL SHUTOFF VALVE BY TURNING HANDLE TO HORIZONTAL POSITION.

WARNING: IF REPELLENT CONTACTS EYES OR SKIN, IRRITATION MAY RESULT. FLUSH AFFECTED AREA WITH WATER IMMEDIATELY AND THOROUGHLY.

RELEASE BOTTLE CLAMP AND UNSCREW BOTTLE FROM RECEPTACLE. EXAMINE BOTTLE SEAT AND 0-RING TO ENSURE THAT TIGHT SEAL WILL BE OBTAINED WITH NEW, BOTTLE.

CAUTION: TIGHTEN RAIN REPELLENT CAN INTO RECEPTACLE FINGER TIGHT. TORQUE IS NOT REQUIRED FOR SEALING. EXCESSIVE TORQUE MAY CAUSE LEAKAGE.

TIGHTEN CLAMP. TURN MANUAL VALVE TO VERTICAL POSITION. PRESSURE GAUGE INDICATES IN SHUTOFF CHECK THAT GREEN BAND.


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ICE & RAIN PROTECTION-B767 series WATER TANK AND DRAIN MAST HEATERS DRAIN MAST HEATERS THE FORWARD AND AFT DRAIN MAST HEATERS ARE POWERED FROM THE GROUND SERVICE BUS. WHEN K205 SENSES AIRPLANE ON THE GROUND THE POWER SOURCE IS SWITCHED TO 28 VAC FROM THE GROUND SERVICE BUS. NOTICE THAT WHILE THE AIRPLANE IS ON JACKS THE HEATERS WILL BE POWERED BY 115 VAC. CAUTION IS ADVISED WHEN WORKING NEAR THE DRAIN MAST.


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ICE & RAIN PROTECTION-B767 series WATER AND WASTE SYSTEM HEATERS HEATER TAPES THE WATER SUPPLY AND DRAIN LINES ARE PROTECTED FROM FREEZING BY THE USE OF RIBBON OR TAPE HEATERS. 115 VOLTS AC POWER IS SUPPLIED FROM THE RIGHT BUS TO THE TAPES THROUGH RELAYS. THE RELAYS ARE ENERGIZED BY THERMOSTATS THAT ARE SET TO COMPLETE THE RELAY CIRCUIT BELOW 40 DEGREES F (4 DEGREES C) AND OPEN THE CIRCUIT ABOVE 60 DEGREES F (16 DEGREES C). SUPPLY/DRAIN PIPE AND WASTE WATER SERVICE HEATERS THE SERVICING CONNECTIONS IN THE WATER SERVICE PANELS AND WASTE SERVICE PANEL ARE HEATED WITH FITTING HEATERS AND A GASKET HEATER RESPECTIVELY. THEY RECEIVE POWER FROM THE 115 VAC RIGHT BUS AND ARE THERMOSTAT CONTROLLED. THE EXCEPTION TO THIS IS THE WASTE SYSTEM DRAIN PIPE GASKET HEATER. IT HAS NO THERMOSTATS AND IS HEATED ANYTIME AC POWER IS APPLIED TO THE AIRPLANE. THERE IS ONE THERMOSTAT INCORPORATED IN THE FILL/FLUSH CONNECTION HEATERS, IT CYCLES OPEN/CLOSE AT 35 DEGREES F (1 DEGREES C). A THERMO SWITCH IS ALSO INCORPORATED AND PROVIDES AN OVERHEAT PROTECTION AT 125 DEGREES F (51 DEGREES C). IF AN OVERHEAT OCCURS THEN THE THERMO SWITCH WILL OPEN AND REMAIN OPEN UNTIL IT IS RESET BY PUSHING ON IT.


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