B767 ATA 30 Student Book

ICE AND RAIN CH 30

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TRAINING MANUAL FOR TRAINING PURPOSES ONLY

TABLE OF CONTENTS ICE AND RAIN TABLE OF CONTENTS ICE AND RAIN ............................................... 2 ACRONYM LIST.................................................................................... 3 GENERAL ............................................................................................. 4 ICE & RAIN PROTECTION SYSTEM ................................................... 6 WING ANTI-ICE COMPONENTS.......................................................... 8 WING THERMAL ANTI-ICE ................................................................ 10 NOSE COWL COMPONENTS ............................................................ 12 NOSE COWL ANTI-ICING .................................................................. 14 ENGINE PROBE HEAT (PT2/TT2) ..................................................... 16 PROBE ANTI-ICING............................................................................ 18 PROBE HEAT CIRCUIT...................................................................... 20 ANGLE OF ATTACK PROBE HEAT (AOA) ........................................ 22 TOTAL AIR TEMP PROBE HEAT (TAT)............................................. 24 WINDOW HEAT CONTROL AND INDICATION ................................. 26 WINDOW HEAT CONTROL AND INDICATION (CONTINUED)......... 28 WINDSHIELD WIPERS ....................................................................... 30 DRAIN MAST / AFT LINE HEATERS.................................................. 36 WATER AND WASTE SYSTEM HEATERS ....................................... 38

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ACRONYM LIST ATA 30 ADC AMB AOA C CB DET EICAS F HP ISO PO PRO PRV PRSOV TAI TAT

AIR DATA COMPUTER AMBIENT ANGLE OF ATTACK DEGREES CENTIGRADE CIRCUIT BREAKER DETECTOR ENGINE INDICATING CREW ALERTING SYSTEM DEGREES FARENHEIT HIGH PRESSURE ISOLATION AMBIENT PRESSURE PROTECTION PRESSURE REGULATOR VALVE PRESSURE REGULATOR SHUT OFF VALVE THERMAL ANTI-ICE TOTAL AIR TEMPERATURE

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ICE AND RAIN PROTECTION INTRODUCTION Ice Protection The ice protection systems prevent icing on critical areas on the airplane and helps maintain aerodynamic efficiency by protecting the: • • • • • • •

Wing Leading Edge Slats Engine Nose Cowls Pitot-static Probes Angle Of Attack Probes Total Air Temperature Probes Flight Compartment Windows Water And Waste Lines

Rain Protection The rain protection systems increase forward visibility through use of: • Windshield Wipers

ICE AND RAIN PROTECTION

RAIN PROTECTION

ICE PROTECTION

WING THERMAL ANTI-ICE

PITOT STATIC PROBE ANTI-ICE

ENGINE INLET THERMAL ANTI-ICE

ANGLE OF ATTACK ANTI-ICE

WINDOW HEAT

WATER AND WASTE ANTI-ICE

TOTAL AIR TEMP PROBE ANTI-ICE

ICE AND RAIN PROTECTION INTRODUCTION B767-3S2F Page - 5

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WINDSHIELD WIPERS

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ICE & RAIN PROTECTION SYSTEM

Windshield Wiper Control Panel Windshield Wiper Selector:

Wing/Engine Anti-ice Control Panel Wing Anti-Ice Switch: • Controls the in-flight operation of both left and right anti-ice valves. • On ground the valves are automatically closed by ground logic regardless of switch position. • VALVE light illuminates when associated valve position disagrees with switch position. Engine Anti-ice Switch (2) • Controls operation of engine anti-ice valves on ground or in flight. • VALVE light illuminates when the cowl valve position disagrees with switch position.

• Three position rotary selector which turns on and controls speed of the windshield wipers. OFF will park the wipers.

Wing Anti-Ice/Window Probe Heat Test Switch Wing Anti-Ice Position: • Hold in this position to test operation of Wing Anti-Ice valves on the ground. During test: • Wing Anti-ice valves open if air pressure is available • Both VALVE lights illuminate on the Wing Anti-ice Panel Window/Probe Heat Position:

Probe Heat Lights (7) Illuminate when: • Aircraft is on ground and engines are not running. • Associated probe is unpowered.

• Hold in this position to test operation of Window and Probe Heat. During test with Window Heat ON: • INOP light illuminates in the four WINDOW HEAT switches. • EICAS message WINDOW HEAT appears. During test on the ground and engines not operating:

Window Heat Control Panel • All probe lights extinguish for a good test. • Controls operation of window heat for associated window • INOP light illuminates when: Switch is OFF System overheat of fault

If a fault is detected: • The faulty probe light remains illuminated.

WING ANTI-ICE ON

L

R

VALVE

L-ENG-R ON

ON

VALVE

VALVE

VALVE

WINDOW HEAT L FWD

FWD

SIDE

ON

ON

ON

ON

INOP

INOP

INOP

INOP

L

R

STALL

R

FO PITOT

L AOA

R AOA

L

L AUX PITOT

R AUX PITOT

L TAT

R TAT

WING ANTI ICE

WINDOW/ PROBE HEAT

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TEST

AIR DATA COMPTR

CAPT PITOT

B767-3S2F

R

SIDE

DUCT LEAK

FUEL QTY

CONFIG T/O

GND PROX

LDG

INOP

YAW DMPR L

R

EQUIP COOL

INOP

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WING ANTI-ICE COMPONENTS Wing Anti-Ice Valve There is one valve for each wing located above the engine strut behind the wing leading edge. It regulates pressure to 23 +/- 3 psig. The valve is solenoid controlled (non-latching) and is pneumatically operated. It has a manual operation drive and lock for maintenance use. To lock, lift knob and rotate 90 degrees clockwise. Wing Overheat Switch (101-170) The switch closes at 190oF (90oC) temperature and is effective only on the ground. There is one in each wing, outboard of the engine strut and just prior to the telescoping duct. It closes the respective tai valve when preset temperature is reached. Pressure Switch One switch is in each wing just upstream of the wing overheat switch. It closes at 34 psi and provides an input to the EICAS computer to display the maintenance message "L (R) WING TAI VALVE". Telescoping Duct One telescoping duct in each wing is located on the outboard side of the #5 and #8 slats. It interconnects the wing feeder duct to the slat spray tube. Flexible Coupling And Spray Tubes A flexible coupling between each slat provides for differential movement. Spray tubes spray bleed air into the leading edge cavity of the three (3) outboard slats only.

WHEN ON GROUND WING A/I CAN ONLY BE OPERATED BY TEST

WING TAI PRESSURE SWITCH

WING TAI OVERHEAT SWITCH

WING ANTI‐ICE IS PROVIDED TO ONLY THE THREE OUTBOARD SLATS

TELESCOPING DUCT WING TAI VALVE

SPRAY TUBE

LEADING EDGE SLAT NOSE SECTION

AIR OUTLET

SPRAY TUBE

MANUAL DRIVE VANE LOCK KNOB AIR EXHAUST

HEX-NUT

(LIFT TO TURN)

Pressure = 23+ or – 3 PSI 34 PSI = Overpressure Defer Closed Only WING ANTI-ICE COMPONENTS B767-3S2F Page - 9

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WING THERMAL ANTI-ICE Electrical Functional Description The system is controlled by a three-position switch: OFF, AUTO and ON. When in flight with the control switch on the pilot's overhead panel selected "ON", a circuit is completed through the air/ground relays, anti-ice valve control relay and a time delay relay to the valve solenoid. When the air/ground relays are in the ground position, the system can only be operated by the test switch on the P61 panel. With the control switch in "auto" the position of the valves will be controlled by inputs from the ice detectors. Ice that occurs on a probe during flight causes the frequency of the probe to decrease. When an ice layer of 0.02 +/-0.0005 inch collects, the heater starts to melt the ice. The heater stops when the frequency returns to its initial value, usually after 7-8 seconds. If ice collects again, this operation occurs again. This is called a "deice cycle". The ice detector counts the number of "de-ice cycles" that occur. When ten "de-ice cycles" occur one after the other, the ice detector gives an output that starts the wing anti-ice system. The wing anti-ice system operates for 180 seconds. If one more "de-ice cycle" occurs during the operation of the wing anti-ice system, the time of 180 seconds starts again. The amber "VALVE" light illuminates for valve position disagreement as provided through the valve closed/not closed switch. The valve closed/not closed switch also activates the EICAS computer which will display a level "C" advisory message for improper valve position. When selected "on", the system will display a "VALVE" light until the time delay relay energizes (2 seconds). When the valve opens, the amber "VALVE" light extinguishes. Pneumatic Functional Description Bleed air is regulated to 23 + 3 psi through the wing tai valve. If manifold pressure down stream of the valve reaches 34 psi due to a malfunction, the EICAS computer will store a maintenance message. When the Wing TAI Switch is selected "ON" and either pneumatic system PRSOV is off, air conditioning pack high flow will be inhibited through their flow control cards.

At the same time a signal is also sent to the Electronic Engine Controls (EEC) for engine trim adjustment. Ground Test Move the test switch on the P-61 panel to the "WING ANTI-ICE" position. The amber "VALVE" light illuminates and extinguishes if air is available in the respective pneumatic manifold. The valve will close after 7 seconds due to a time delay ground test relay in the P33 panel.

WING ANTI-ICE L

L-ENG-R

R

PACK FLOW CONTROL-L

TEST 1 – VALVE LIGHT ON FOR 1 to 3 SEC 2 – VALVE LIGHT OFF FOR 10 to 20 SEC 3 – PRESSURE GAUGE SHOWS 20‐28 PSIG 4 – EICAS MSG “WING ANTI‐ICE”

T

T 200 F (93 C)

*

2.5 S

2.5 S

RIGHT WING TAI OVERHEAT SW R WING ANTI-ICE (Y) L WING ANTI-ICE (Y)

R WING TAI VALVE (W) L WING TAI VALVE (W)

*

10 S NVM LATCH

P

10 S

P 34 PSI

RIGHT WING TAI PRESSURE SW

L/R EICAS CMPTR OFF

CLOSED

MASTER DIM AND TEST ON

NOT CLOSED

RIGHT VALVE LT

R WING TAI DISAGREE RELAY

P 10 PSI

R WING TAI VALVE INSTR LTS

MASTER DIM AND TEST ON

LEFT VALVE LT

ENG EEC DISCRETE INPUTS-R

L WING TAI DISAGREE RELAY

CLOSED AIR NOT CLOSED

AIR

T

28V DC

D

WING ANTI-ICE

GND

WING ANTI-ICE SW

SYS NO. 2 AIR/GND RELAY

WING AND ENG ANTI-ICE CONT PNL

P11 PANEL

2 SEC

WING TAI CONT RELAY

WING TAI CONT T/D RELAY

GND


P 10 PSI

L WING TAI VALVE

P

WING ANTI-ICE OFF WINDOW/PROBE HT

P 34 PSI

LEFT WING TAI PRESSURE SW

PITOT STATIC PROBE WINDOW HEAT PITOT STATIC PROBE WINDOW HEAT WING TAI/WINDOW PROBE HT SW

(CONDITION) WING ANTI‐ICE ON IN GROUND TEST

TEST PNL

WING THERMAL ANTI-ICE B767-3S2F Page - 11

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T

T 200 F (93 C)

LEFT WING TAI OVERHEAT SW

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ENGINE ANTI-ICE NOSE COWL COMPONENTS Nose Cowl Thermal Anti-Icing Valves The Nose Cowl TAI valve located above each engine is accessed in the engine strut through the same openings as the air supply regulating and shutoff valve (PRSOV). It regulates pressure to 23 +/-3 psig and operates the same way as the wing anti-ice valve. It can be manually locked either open or closed. However delta's MEL specifies dispatch in the closed position only. Cowl Thermal Anti-Ice Pressure Switch A pressure sensing switch, in the cowl tai supply duct at the top of the engine strut, near the leading edge of the wing, closes at 30 psi. It completes a circuit to the EICAS computer to display the status/maintenance message "L (R) ENG TAI VALVE". Nose Cowl Thermal Anti-Ice Duct Bleed air is tapped off downstream of the pre-cooler prior to the pressure regulating and shutoff valve. The duct extends along the top of the engine strut to the nose cowl spray ring. The air exists through the exhaust vent at the bottom of the nose cowl.

Spring Loaded Closed Regulates 20‐28 PSI SOLENOID VALVE (ON/OFF)

PILOT ASSEMBLY VALVE BODY ACTUATOR OPEN CLOSED NORMAL LOCKED OPEN

LIMIT SWITCHES

LOCKED CLOSED

POSITION INDICATOR & MANUAL DRIVE

ELECTRICAL CONNECTION

HOUSING

FILTER (SUPPLY AIR) LOCKOUT KNOB

FLATS FOR WRENCH (INSTALLATION & REMOVAL)

NOSE COWL TAI VALVE, LEFT SIDE VIEW VALVE MAY BE LOCKED IN THE OPEN OR CLOSED POSITION

THREADED NIPPLE COWL TAI PRESSURE SWITCH NOSE COWL TAI VALVE RIGHT SIDE VIEW

Normally Open Closes @ 30 PSI

NOSE COWL COMPONENTS B767-3S2F Page - 13

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ENGINE ANTI-ICE NOSE COWL ANTI-ICING Electrical Functional Description The three-position control switches are located on the P5 pilot's overhead panel. The switches are labeled "OFF", "AUTO" and "ON". The amber "valve" light illuminates to indicate valve position disagreement. The valve will be commanded open with the switch in the "ON" position or in the "AUTO" position with ice present. After a 2-second time delay, the engine tai control time delay relay energizes, the valve opens and the amber light extinguishes. This relay also enables the high stage control circuit. Selection of engine anti-ice causes EICAS to display the tai readout in green above the appropriate N1 display. With the control switch in "AUTO" the position of the valve will be controlled by inputs from the ice detectors. Ice that occurs on the probe during flight causes the frequency of the probe to decrease. When an ice layer of 0.02 +/-0.0005 inch collects, the heater starts to melt the ice. The heater stops when the frequency returns to its initial value, usually after 7-8 seconds. If ice collects again, this operation occurs again. This operation is called a "de-ice cycle". The ice detector counts the number of "de-ice cycles" that occur. When two "de-ice cycles" occur one after the other, the ice detector gives an output that starts the engine anti-ice system. The engine anti-ice system operates for a time of 180 seconds. If one more "de-ice cycle" occurs during the operation of the engine anti-ice system, the time of 180 seconds starts again. If more than 15 seconds are necessary to melt the ice on the first "de-ice cycle", the engine anti-ice system starts after only one "de-ice cycle". The engine anti-ice system does not operate on the ground when the engine anti-ice switch is in the "AUTO" position. Indication is provided on the P5 overhead and EICAS when switch position and valve position disagree or when there is an "OPEN" in the valve position indication circuit. Valve position disagree indication or open in the valve position indication circuit is provided by an amber "valve" light within the control switch. A level "C" EICAS message will display, "L (R) ENG ANTI-ICE".

WING ANTI-ICE

L

L-ENG-R

R

A

INDICATES VALVE AMBER SEE A

NOSE COWL TAI VALVE ‐ Limits to 23 PSI ‐ Can be locked Open or Closed

WING AND ENGINE ANTI-ICE CONTROL PANEL (P5)

CONTROL CIRCUIT

SEE B

EICAS CRT

NOSE COWL TAI DUCT

COWL TAI PRESS. SWITCH

EICAS COMPUTERS

NOSE COWL TAI PRESSURE SWITCH

AIR SUPPLY PRESSURE REG/ SHUTOFF VALVE

NOSE COWL TAI VALVE

(T/R)

COWL TAI DUCT PRECOOLER

OVERBOARD

FAN FAN AIR MODULING VALVE

NOSE COWL TAI VALVE

PRV

EXHAUST VENT

HP SOV

B IP 8th NOSE COWL SPRAY RING

NOSE COWLING ANTI-ICING B767-3S2F Page - 15

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HP 14th

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ENGINE INLET OVERHEAT SWITCH GENERAL The Engine inlet overheat temperature switch protects the EEC from excessive heat. It is located under the right fan cowl on the fan cowl support beam. The Engine inlet overheat temperature switch will close the Anti-ice valve and give and EICAS message “L(R) COWL DUCT LEAK” >250 F. The temperature switch can be reset by pushing and releasing the Engine Anti-Ice Switch with Temp <250 F.

The Engine Inlet Overheat Temperature Switch will close the Anti‐ice valve and give an EICAS Message “L(R) COWL DUCT LEAK” >250 F Can be reset by pushing and releasing the Engine Anti‐Ice Switch with Temp <250 deg F.

ENGINE COWL OVERHEAT SWITCH

FAN COWL SUPPORT BEAM

Protects EEC from excessive heat

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ENGINE PROBE HEAT COMPONENT LOCATIONS Locations TAT There are two TAT Probes located on the sides of the fuselage below the aircraft windows. The TAT probes are not heated on the ground. They are heated in air or in test with 115 VAC. ANGLE OF ATTACK There are two AOA Probes located in between the upper and lower Pitot Static Probes. The AOA probes are not heated on ground unless engines are running or in test. Heat on ground with engine N2 > 50% is with 115 VAC. In Air they are also heated with 115 VAC. PITOT STATIC PROBES There are four Pitot Static Probes located on both sides of the fuselage below the windows. The two upper probes on both sides are the primary probes and the two lower probes on both sides are the alternate probes. Both sets of probes have both Pitot and two Static ports. The left probes are interchangeable and the right probes are interchangeable. However, the probes are not interchangeable from left to right sides. The Pitot Probes are not heated on ground unless engines are running. They have high heat in air and are heated with 200 VAC, and Low heat on ground with 115 VAC with the engines N2 > 50%.

ENGINE PROBE HEAT COMPONENT LOCATIONS B767-3S2F Page - 19

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PROBE ANTI-ICE FUNCTIONAL DESCRIPTION General The probe anti-ice system will give a specific probe fault on EICAS if any single probe has faulted. If two or more probes have a fault in any system you will get an EICAS message that says “PROBE HEAT (L,C,R)”

SINGLE FAULT = SPECIFIC PROBE FAULT ON EICAS TWO OR MORE PROBES FAULT = PROBE HEAT _ (L,C,R)

HEATER OFF HEATER ON

F/O PITOT C

TO HIGH HEAT IND CIRCUIT

F/O PITOT/STATIC CURRENT SENSING (P33)


R AUX PITOT C


AUX P/S CURRENT SENSING (P33)

HEATER OFF

R AOA PROBE C

1

HEATER ON R AOA PROBE CURRENT SENSING (P33) HEATER OFF

EITHER ENG

HEATER ON

N2 >50%

L TAT PROBE CURRENT SENSING (P33)

L PROBE HT N2 (P33)

TWO OR MORE ARE TRUE

AIR/TEST

GND

2

SYS 2 AIR/ GROUND (P33)

1


HEATER OFF HEATER ON CAPT P/S CURRENT SENSING (P33)

HEATER ON

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CAPT PITOT C

TO HIGH HEAT IND CIRCUIT 1

L (R) EICAS COMPUTERS (E8-1) CONNECTED ONLY IF TWO TAT PROBES INSTALLED

2

NOT CONNECTED IF TWO TAT PROBES INSTALLED

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TAT PROBE C


L AOA PROBE CURRENT SENSING (P33)

ATA 30-20

L TAT PROBE C

L AOA PROBE C

HEATER OFF

PROBE ANTI-ICE FUNCTIONAL DESCRIPTION B767-3S2F

PROBE HEAT C

L AUX PITOT C


L AUX P/S CURRENT SENSING (P33)

R TAT PROBE C


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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), one each side, located between the pitot static probes, have electrically heated vanes and casings.

Total Air Temperature Probe The total air temperature probe, (one only), 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 to allow for more accurate sensing when the airplane is stationary (runway prior to take-off). All probes can be accessed externally.

DOO RS ENT RY

EM ER DOORS

CARG O DOOR S

ACCE SS DO ORS

CAPT PITOT

FO PITO T

L AOA

R A OA

L A UX PITOT

R AUX PITOT

L T AT

R T AT

STAB TRIM

SPOILER S

A UTO SPDB RK

UNSC HED ST AB TRIM

RUD DER RATI O

AN TIS KID

IRS MODE SEL N

W

DSPL SEL PPO S WIN D TK/GS BRT

HDG

SYS DSP L C L R

1

N 2

3

W 4

H 5

E 6

7

S 8

9

ENT

0

C ALIG N

R ALIGN

ON DC

ON DC

ON DC

DC FAIL

DC FAIL

DC F AIL

OFF

ON COMMAND

ELEC ENG CONT

TEST

L ENG

P R I M A R Y D E M A N D

ON

ALTN

SYS PRESS

QTY

QTY

OFF

PUMPS C 1-ELEC-2

R ENG ON

ON

PRESS PRESS

PRESS

OVHT

OVHT

OVHT

OVHT

ELEC

AIR

ELEC

PRESS

PRESS

PRESS

OVHT

OVHT

OVHT

AUTO AUTO AUTO ON ON OFF ON OFF

WINDOW/ PROBE HEAT

0 F F APU GEN EXT PWR O F ON F

BUS TIE

HYD

ON

OFF

ON

D I S C H

PRESS

OFF

WING ANTI ICE

STBY POWER AUTO BAT

BAT

ON

SYS PRESS

QTY

EVACUATION SIGNAL

USB OFF AM

R

ALTN

SYS PRESS

P R I M A R Y D E M A N D

AUTO

ON

BUS TIE

AVAIL

AUTO ISLN

ISLN UTILITY BUS L R

L BUS BUS OFF

L GEN CONT O F ON F

ON

ON

OFF

OFF

R BUS BUS OFF

GEN DRIVE DISC L R

OFF

TOTAL A IR TEMP PROBES (2)

R GEN CONT O F ON F

DRIVE

DRIVE APU

ON

START

RUN FAULT

TEST

ERASE

HEADSET 600 OHMS COCKPIT VOICE RECORDER

PANEL/FLO OD

GLARESHIELD

AILE STAND ON

OFF

OFF TAXI RUNWAYTURNOFF OFF L OFF R ON

ON

PROBE ANTI-ICING B767-3S2F Page - 23

R TAT

INOP

L ON

L TAT

HORN SHUTOFF

ON

INOP INOP

R AOA

SQUELCH

ANTI SKID

ON

L AOA

EVAC P U S H

H F

ON

ENG EEC PRO BE

FO PITOT R AUX PITOT

PRESS TO TEST

ARM

FAULT FAULT FAULT ALIGN NAVATT ALIG NNAVATT ALIG NNAVATT OFF OFF OFF

YAW DAMPER L R

AI L LOCK

MA CH PRO BES

CLR

L ALIG N

CAPT PITO T L AUX PITOT

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PROBE HEAT CIRCUIT Pitot-Static Probe Heat Each of the 4 pitot-static probe heat circuits operate in the same way. The graphic shows the captain's & first officer's probe circuits and the engine N2 circuits. The air/ground relays and the probe heat N2 relays provide automatic switching of heat to the probes. For high heat (flight or system test) the probes receive phase to phase voltage (208). For low heat (ground & engine N2 greater than 50%) the probes receive phase to ground voltage (115). For no heat (ground & no engine running) the heat circuit is open. The current sensing relays determine if the probes are being heated. If no current is sensed, a ground turns on the appropriate pitot heat monitor light on the P5 panel. This same ground signals the EICAS computers to generate the appropriate level "C" message. If a heater is on high heat during a low heat condition, the current sensing relay, air/ground relay, and probe heat test relay supply a signal to EICAS to generate the appropriate maintenance message.

Probe Heat Test The "WINDOW/PROBE HEAT" test is normally accomplished with engines off. The test switch on the P61 panel, forces all the probe heat circuits into the air position. Any probe heat-off displays on the P5 panel and on EICAS should extinguish. If, during the probe heat test, a probe heat circuit fails, EICAS will provide an advisory message. One of five messages will be displayed for the pitot-static probes -"CAPT PITOT", "L AUX PITOT", "F/O PITOT", "R AUX PITOT", or "PROBE HEAT" if two or more are faulty. If a AOA probe heat circuit fails "L AOA PROBE" or "R AOA PROBE" will display. If a TAT probe heat circuit fails "TAT PROBE" will be displayed.

•

PITOT HEAT LOW 115 VAC AIRCRAFT ON GROUND WITH ENGINES RUNNING N2 > 50%

28V DC BAT BUS R PROBE HT IND

HEATER OFF ADC

P11

AIR/TEST HEATER ON TEST R PROBE HT TEST (P33)

115V AC R BUS F/O B PITOT PROBE HT

AIR/TEST

115V AC R BUS F/O A PITOT PROBE HT P6

GND

GND

N2 >50%

SYS 1 AIR/GND (P33)

R PROBE HT N2 (P33)

R N2 ENGINE SPEED CARD (P50) WING TAI/ WINDOW PROBE HT

ON GND

10S

N2 >50% L N2 ENGINE SPEED CARD (P50)

PROBE HEAT CIRCUIT ATA 30-30 3/28/14

NVM

L AND R EICAS CMPTR (E8-1)

TEST (P61)

Page - 25

MD&T PROBE HT EICAS IND (C)

F/O PITOT/ STATIC PROBE N2 >50%

B767-3S2F

F/O P/S CURRENT SENSING (P33)

SYS 2 AIR/GND (P33)

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F/O PITOT HEAT (M)

F/O PITOT ANNUNCIATOR (P5)

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ANGLE OF ATTACK PROBE HEATING (AOA) Angle Of Attack (AOA) Probe Heat The probes are heated with 115 volt AC power in the air and are not heated on the ground until the engines are operating. When an AOA heat current sensing relay fails to sense current through the heater the appropriate AOA annunciator light on the P5 panel is illuminated and the EICAS displays the appropriate level "C" message.

115V AC R BUS

VANE

PROBE HT R AOA HEATER OFF

P6

AIR/TEST CASE GND

ADC

SYS 2 AIR/GND

28V DC BAT BUS RIGHT PROBE HT IND R AOA PROBE CUR SENSING (P33)

P11

N2 >50%

R AOA SENSOR

R PROBE HT N2 (P33) PROBE HEAT EICAS IND

MD&T

R AOA

FOR NORMAL OPERATIONS THE AOA PROBE IS HEATED IN THE AIR (or TEST) Or if ENG N2 is >50% ON GND

ANGLE OF ATTACK PROBE HEATING (AOA) B767-3S2F Page - 27

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TOTAL AIR TEMP PROBE HEAT (TAT) Total Air Temperature (TAT) Probe Heat The two TAT probes are heated with 115 volts AC power. In the air the air/ ground relay K514 completes the circuit through the TAT heater current sensor relay K411. With current flowing through the current sensing transformer the circuit to the TAT light on the P5 panel and EICAS is inhibited. With loss of current through K411 the light illuminates and an EICAS advisory message appears. On the ground with either engine running the probe is not heated but the EICAS message is inhibited and the light is extinguished.

ENGINE HEATER OFF AIR DATA/L C R 28V DC STBY BUS LEFT PROBE HEAT IND

HEATER ON

MD&T

>50 PERCENT RPM TAT PROBE HT

TAT PROBE CURRENT SENSING

ANNUNCIATOR

GND

PROBE HEAT EICAS MESSAGE

SYS 2 AIR/GND

Current Sense Relay Only Operates in AIR

GND SYS 1 AIR/GND TAT PROBE

P6

FOR NORMAL OPERATIONS THE TAT PROBE IS ONLY HEATED IN THE AIR (or TEST)

TOTAL AIR TEMPERATURE PROBE HEAT (TAT) B767-3S2F Page - 29

L TAT

AIR/TEST

P11

115V AC L BUS LEFT TAT PROBE HEAT

AIR/TEST

SPEED

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B767-3S2F Page - 30

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WINDOW ANTI-ICE WINDOW HEAT CONTROL AND INDICATION

Windows #2 & 3

General

Windows #2 & 3 use a different scheme to regulate temperature. The sensor in the window will switch on the full single-phase AC power at 100oF and turn the power off at 105oF. Under normal in-flight conditions, this would roughly approximate one minute on - one minute off.

Window heat is provided through 2 controllers with "BITE" in each. Each control unit has 3 channels. One channel controls window #1, and the remaining 2 channels control the opposite #2 & 3 side windows. The controllers are located in the main equipment center E2-1 (#2) and E 1-2 (#1) shelves. "BITE" 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 #2 windows use a coiled extension cord for power and sensing leads that allows the window to be opened and closed. Power for the left forward and right side window heat control unit comes from the left main buses. The #1 window uses two phase 115 volt AC power to maintain a regulated 95oF (35oC). #2 & 3 windows use a single phase AC power from a separate circuit. These windows use a cycling full on and off circuit to maintain 100oF (37.8oC). Overheat for any of the windows is annunciated at 110oF (43.3oC). Window #1 Window #1 uses two phase power to generate a sawtooth 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 in slowly on initial power-up due to a 6 minute ramp generator. The heat command is superimposed on the sawtooth generator wave. This clips the signal into a series of "ON" and "OFF" commands. These commands are used by the silicon controlled rectifier to pass AC power to the window.

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 sensors circuits used primarily for voltage and noise isolation during signal transfer.

WINDOW HEAT CONTROL AND INDICATION B767-3S2F Page - 31

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B767-3S2F Page - 32

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WINDOW HEAT CONTROL AND INDICATION (CONTINUED) BITE All 3 window channels have taps into the "BITE" circuit. These taps measure power on, sensor resistance, output current, and asymmetry. Using logic 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 (110oF), 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 inoperative relay(s).

Window Temperature Sensor Connections Terminal blocks TB322 and TB324 are located on the forward outboard stanchions of E1 and E2. Access is through the e/e compartment. Dispatch Deviation Window Heat Light "INOP": • Verify that the appropriate window heat EICAS message appears with window heat switches in the OFF position

J9

L WDO HT NO. 3 115V AC R BUS L WDO HT NO. 2 ÷A

C

÷B

D

J12 COATING C

J10 CONT SNSR

RSV

R WINDOW HT NO. 1

J11 TB 324

P37 PANEL

1

EICASINPUT L SIDE WINDOW

J8

INOP

A

COATING D

ON W

W

ON A

MASTER DIM ANDTEST

A

INTERNALS SAME AS L FWD & R SIDE WINDOW HEAT CONT UNIT

E

A

INOP L SIDE CONTROL SW INOP

J7 CONT SNSR J6

RSV TB 324 1

J4 J5

INSTR LTS EICAS INPUT

W

R FWDWINDOW

ON

COATING

J3

E

CONT SNSR

B

J2

RSV A

SPARE

L WINDOW 2 J1

ON W

SPARE

L WINDOW 3

A

B

INOP

TB 324 1

R FWD CONTROL SW

SPARE

R WINDOW 1

WINDOW HEAT CONT PNL 28V DC L BUS

WINDOW HEAT L FWD & R SIDE WINDOW HEAT TEST

P11 PANEL

1

TB 324 AND TB323 FOR PICKING SPARE SENSORS ARE LOCATED ON THE SIDES OF THE E1 & E2 RACKS.

OFF

WINDOW/PROBE HEAT WINDOW/PROBE HEAT SW

MISC TEST PNL

R FWD & L SIDE WINDOW HEAT CONT UNIT

Window Heat is Divided and controlled: L Fwd and R Side Windows And R Fwd and L Side Windows

WINDOW HEAT CONTROL AND INDICATION (CONTINUED) B767-3S2F Page - 33

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B767-3S2F Page - 34

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WINDSHIELD WIPERS Windshield Wiper/Converter Two windshield wiper assemblies are used to assist in moisture removal from the #1 left and right wind- shields. 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 windshield is 15 lbs. 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 THE WIPER BLADE TO MOVE ON A DRY WINDSHIELD. Electrical Functional Description A three position rotary switch ("HIGH", "LOW", "OFF") located on the bottom center of the P5 panel connects 28 volt dc power to ground. Power through the switch comes from both buses (left & 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 28 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 captain's and first officer's windshield wipers are controlled from the same switch. Wafers within the switch provide contact for the various circuits operating the system.

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

MOTOR CONVERTER

WIPER ARM ACCESS PANEL LIFT BLOCK ASSEMBLY

WINDSHIELD WIPER CONTROL PANEL P5 PILOT'S OVERHEAD PANEL

WINDSHIELD WIPERS B767-3S2F Page - 35

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WIPER BLADE IN PARK POSITION

B767-3S2F Page - 36

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DRAIN MAST / AFT LINE HEATERS Drain Mast Heaters The forward and aft drain mast heaters are powered from the 115 volt AC ground service bus. An air/ground relay in the system completes a circuit from the 28 volt AC ground service bus when the relay is in the ground position. In the air 115 volts AC is applied directly to the heaters from the ground service bus. Aft Line Heaters Several aft water line heaters are powered from the 115 volt AC ground handling bus and operate on the ground when the bus is powered. Heater tape control thermostats set at 40-60oF control operation of the tape heaters. Dispatch Deviation Drain Mast(s) heater "INOP": • Close affected galley, wash basin water or toilet supply shut-off valves

(FUSELAGE) (CEILING) (FWD BULKHEAD)

(AFT BULKHEAD)

MID TRANSVERSE DRAINS

FWD TRANSVERSE DRAIN

AFT TRANSVERSE DRAIN

(MAIN DECK FLOOR)

LEAD WIRES THERMOSTAT

CONTROL THERMOSTAT

HEATER TAPE (PRESSURE BULKHEAD)

WATER FILL CONNECTION THERMOSTAT

(FUSELAGE) FWD DRAIN MAST

AFT DRAIN MAST

CONTROL THERMOSTATS

WASTE TANK FITTING HEATER

ELECTRICAL LEADS

DRAIN MAST EXTENSION TUBE HEATER TAPE

HEATING GASKET HEATING GASKET LEAD

WATERLINE RIBBON HEATER TAPE

HEATER TAPE

TERMINAL BUTTON

DRAIN MAST ADHESIVETAPE LEAD WIRES WASTE TANK SERVICE PANEL

DRAIN MAST / AFT LINE HEATERS B767-3S2F Page - 37

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WATER LINE HEATER TAPE

B767-3S2F Page - 38

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WATER AND WASTE SYSTEM HEATERS Water / Waste 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 are heated directly from the 115 volt AC right bus and are not thermostat controlled except for the water fill/flush connections which have thermostats. There is one thermostat incorporated in the fill/flush connection heaters which cycles open/close at 35oF (1oC). A thermoswitch is also incorporated and provides an overheat protection at 125oF (51oC). If an overheat occurs then the thermoswitch will open and remain open until it is reset by pushing on it. Fwd Water Line Heater Tapes The fwd water 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 40oF (4oC) and open the circuit above 60oF (16oC). Line 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 40oF (4oC) and open the circuit above 60oF (16oC).

42.F (6.C)

T

115V AC

WATER LINE WATER LINE HTR TAPE HEATERS RELAY

HTR TAPE W/CTRL THERMOSTAT 35.F (1.C)

T

40.F (4.C)

T

T 125.F (52.C)

WATER FILL FITTING HTR

HTR TAPE CTRL THERMOSTAT

35.F (1.C)

T

GASKET HTR

T

125.F(52.C) 375.F(190.C)

28V AC 115V AC

WASTE TANK SVCE FITTING HTR

GND

DRAIN MAST AIR


DRAIN MST HTR (EXAMPLE)

HEATING GASKET FORWARD DRAIN MAST

B91 THERMOSTAT WATER DRAIN SYSTEM

WATER AND WASTE SYSTEM HEATERS B767-3S2F Page - 39

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B767 ATA 30 Student Book

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