B767 ATA 30 Student Book

TRAINING MANUALFOR TRAINING PURPOSES ONLY

B767-3S2F CH 30-00 Page - 1 28 Mar ,2014 EFF - ALL

ICE AND RAINCH 30


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



ACRONYM LIST ATA 30

ADC AIR DATA COMPUTERAMB AMBIENTAOA ANGLE OF ATTACKC DEGREES CENTIGRADECB CIRCUIT BREAKERDET DETECTOREICAS ENGINE INDICATING CREW ALERTING SYSTEMF DEGREES FARENHEITHP HIGH PRESSUREISO ISOLATIONPO AMBIENT PRESSUREPRO PROTECTIONPRV PRESSURE REGULATOR VALVEPRSOV PRESSURE REGULATOR SHUT OFF VALVETAI THERMAL ANTI-ICETAT TOTAL AIR TEMPERATURE



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 INTRODUCTION

ICE AND RAIN PROTECTION

ICE PROTECTION

WING ENGINE INLET THERMAL THERMAL ANTI-ICE ANTI-ICE

WINDOW HEAT

RAIN PROTECTION

WATER AND WINDSHIELD

WASTE WIPERS

ANTI-ICE

PITOT ANGLE TOTALSTATIC OF AIR TEMPPROBE ATTACK PROBEANTI-ICE ANTI-ICE ANTI-ICE



ICE & RAIN PROTECTION SYSTEM

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.

Probe Heat Lights (7)

Illuminate when:

• Aircraft is on ground and engines are not running. • Associated probe is unpowered.

Window Heat Control Panel

• Controls operation of window heat for associated window • INOP light illuminates when:

Switch is OFF System overheat of fault

Windshield Wiper Control Panel

Windshield Wiper Selector:

• 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:

• 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:

• All probe lights extinguish for a good test.

If a fault is detected:

• The faulty probe light remains illuminated.



ICE AND RAIN PROTECTION SYSTEM

WING ANTI-ICE L-ENG-R

ON ON ON

L R VALVE VALVE

VALVE VALVE

WINDOW HEAT

L R

SIDE FWD FWD SIDE

ON ON ON ON

INOP INOP INOP INOP

CAPT F O PITOT PITOT L AOA R AOA

L AUX R AUX PITOT PITOT L TAT R TAT

L

L

WING

AIR DATA COMPTR

STALL

TEST R CONFIG

T/O GND PROX

INOP R LDG

YAW DMPR ANTI ICE

WINDOW/ PROBE HEAT

DUCT LEAK L EQUIP COOL

FUEL QTY R INOP


B767-3S2F ATA 30-10 Page - 8 3/28/14 EFF - ALL

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.



WING ANTI-ICE COMPONENTS

WING TAI PRESSURE SWITCH

WING TAI

OVERHEAT SWITCH

TELESCOPING

DUCT

SPRAY WING TAI VALVE

LEADING EDGE SLAT NOSE

SECTION

AIR OUTLET

SPRAY TUBE

AIR EXHAUST

TUBE

MANUAL DRIVE

VANE LOCK KNOB HEX-NUT

(LIFT TO TURN)

Pressure = 23+ or – 3 PSI34 PSI = OverpressureDefer Closed Only

WING ANTI‐ICEIS PROVIDED TOONLY THE THREEOUTBOARD SLATS

WHEN ON GROUNDWING A/I CAN ONLYBE OPERATED BY TEST



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 "de-ice 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 THERMAL ANTI-ICE


L R

PACK FLOW CONTROL-L

2.5 S

2.5 S

R WING ANTI-ICE R WING TAI (Y) VALVE (W)

L WING ANTI-ICE L WING TAI (Y) VALVE (W)

10 S NVM

LATCH 10 S

T

T 200 F (93 C)

RIGHT WING TAI OVERHEAT SW

P

P 34 PSI

RIGHT WING TAI

INSTR LTS

28V DC

WING ANTI-ICE

P11 PANEL

OFF

ON RIGHT VALVE LT

ON LEFT VALVE LT

WING ANTI-ICE SW

WING AND ENG ANTI-ICE CONT PNL

WING ANTI-ICE OFF WINDOW/PROBE HT

WING TAI/WINDOW PROBE HT SW

TEST PNL

MASTER

DIM AND TEST

R WING TAI DISAGREE RELAY

MASTER

DIM AND TEST

L WING TAI DISAGREE RELAY

AIR

GND

SYS NO. 2 AIR/GND RELAY

PITOT STATIC PROBE

WINDOW HEAT

PITOT STATIC PROBE

WINDOW HEAT

L/R EICAS CMPTR

ENG EEC DISCRETE INPUTS-R

AIR

T

D GND

2 SEC SYS NO. 2 AIR/GND RELAY

WING TAI WING TAI CONT CONT RELAY T/D RELAY

PRESSURE SW

CLOSED

NOT CLOSED

P 10 PSI

R WING TAI VALVE

CLOSED

NOT CLOSED

P 10 PSI

L WING TAI VALVE

P

P 34 PSI

LEFT WING TAI PRESSURE SW

T

T 200 F (93 C)

LEFT WING TAI OVERHEAT SW

**

(CONDITION)WING ANTI‐ICE ONIN GROUND TEST

TEST1 – VALVE LIGHT ON FOR 1 to 3 SEC2 – VALVE LIGHT OFF FOR 10 to 20 SEC3 – PRESSURE GAUGE SHOWS 20‐28 PSIG4 – EICAS MSG “WING ANTI‐ICE”



ENGINE ANTI-ICENOSE 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.



NOSE COWL COMPONENTS

SOLENOID VALVE (ON/OFF)

PILOT ASSEMBLY

VALVE BODY

ACTUATOR OPEN

CLOSED

LOCKED OPEN

ELECTRICAL CONNECTION

HOUSING FILTER

(SUPPLY AIR)

FLATS FOR WRENCH (INSTALLATION & REMOVAL)

THREADED NIPPLE

COWL TAI PRESSURE SWITCH

NORMAL

LOCKED CLOSED

NOSE COWL TAI VALVE RIGHT SIDE VIEW

LIMIT SWITCHES

POSITION INDICATOR & MANUAL DRIVE

LOCKOUT KNOB

NOSE COWL TAI VALVE, LEFT SIDE VIEW

VALVE MAY BE LOCKED IN THE OPEN OR CLOSED POSITION

Spring Loaded ClosedRegulates 20‐28 PSI

Normally OpenCloses @ 30 PSI



ENGINE ANTI-ICENOSE COWL ANTI-ICING


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".



NOSE COWLING ANTI-ICING


L RA

WING AND ENGINE ANTI-ICE SEE A

SEE B

NOSE COWL TAI DUCT

NOSE COWL TAI PRESSURE SWITCH

EICAS CRT EICAS COMPUTERS

CONTROL PANEL (P5)

COWL TAI PRESS. SWITCH

COWL TAI DUCT

CONTROL CIRCUIT

NOSE COWL TAI VALVE

PRE-

AIR SUPPLY PRESSURE REG/ SHUTOFF VALVE

OVER-

NOSE COWL TAI VALVE

B

NOSE COWL SPRAY RING

FAN

FAN AIR MODULING VALVE

EXHAUST VENT

COOLER BOARD

IP HP 8th 14th

PRV

HP SOV

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

Closed

(T/R)

INDICATESVALVE AMBER



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.



ENGINE COWLOVERHEATSWITCH FAN COWL

SUPPORTBEAM

Protects EEC from excessive heat

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



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



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)”



PROBE ANTI-ICE FUNCTIONAL DESCRIPTION

HEATER OFF

HEATER ON

F/O PITOT/STATIC CURRENT SENSING (P33)

HEATER OFF

HEATER ON

R AOA PROBE CURRENT SENSING (P33)

HEATER OFF

HEATER ON

L TAT PROBE CURRENT SENSING (P33)

HEATER OFF

HEATER ON

L AUX P/S CURRENT SENSING (P33)

TO HIGH HEAT IND CIRCUIT

HEATER OFF

HEATER ON

AUX P/S CURRENT SENSING (P33)

EITHER ENG

N2 >50%

L PROBE HT N2 (P33)


HEATER OFF

HEATER ON

L AOA PROBE


1

AIR/TEST

GND 2

SYS 2 1 AIR/ GROUND (P33)


F/O PITOT C

R AUX PITOT C

R AOA PROBE C

R TAT PROBE C

TWO OR MORE PROBE ARE HEAT C TRUE

L TAT PROBE C

TAT PROBE C

L AUX PITOT C

L AOA PROBE C

HEATER OFF CURRENT SENSING (P33) CAPTPITOT C

HEATER ON TO HIGH HEATIND CIRCUIT

CAPT P/S CURRENT L (R) EICAS COMPUTERS (E8-1)

SENSING (P33) 1 CONNECTED ONLY IF TWO TAT PROBES INSTALLED

2 NOT CONNECTED IF TWO TAT PROBES INSTALLED

SINGLE FAULT = SPECIFIC PROBE FAULT ON EICAS

TWO OR MORE PROBES FAULT = PROBE HEAT _ (L,C,R)



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.



PROBE ANTI-ICING

WINDOW/PROBE HEAT

WINGANTI ICE

TEST

HS

EVACPRESS TO TEST

PU

SHUTOFFHORN

EVACUATION SIGNALCOMMANDON

ARM

OFF

OFFTAXI RUNWAYTURNOFF

AILE STANDGLARESHIELDPANEL/FLO OD

ON

ON

OFF OFF

RLOFF

ON

RUN

FAULT

APUOFF

ONSTART

DRIVEON

OFF

RL

UTILITY BUSL R

GENCONTGEN

BUS TIE

RL

OFF

ONOFFDRIVE

BUSOFF

ON

ON

OFF

ISLN

AUTO

ISLN

AVAIL

ONOFF

CONT

AUTO

GEN DRIVE DISC

L BUSBUSOFF

BUS TIE

R BUS

APU GEN EXT PWR

ON

DOO RSENT RY

CAPTPITOT

L AUXPITOT

STABTRIM

ST AB TRIMUNSC HED

DOORSEM ER

PITO T F O

R AUXPITOT

SPOILER S

RUDDERRATI O

CARGODOORS

L AOA

AUTOSPDB RK

AN TISKID

DO ORSACCESS

R AOA

AI LLOCK

ONAUTO

OFFONAUTO

OFF

PRESS

OVHT

PRESS

OVHT

PRESS

OVHT

OVHTOVHTOVHT

ON

PRESS

ON

PRESS

ON

PRESS

SYSPRESS

QTY

SYSPRESS

QTY

SYSPRESS

QTY

PUMPSHYDC

1-ELEC-2L

ENGR

ENG

ON

PRESS

OVHT

ELECELEC AIR

ONAUTO

OFF

PRIMARY

PRIMARY

D

DEMAN

D

DEMAN

RCL

DSPL SEL

ATTNAV

OFF

ALIGNATTNAV

OFF

ALIGN

6E

4W

2N

ATTNAV

NW

PPOS WIN D

TK/GS HDG

SYS DSP L

RLC

5H

8S

97

31

0 CLRENT

BRT

IRS MODE SEL

OFF

ALIGN

DC FAIL

ON DC

FAULT

ALIGN

DC FAIL

ON DC

FAULT

ALIG N

DC FAIL

ON DC

FAULT

ALIGN

TEST ERASE

HEADSET600 OHMS

COCKPIT VOICE RECORDER

L RYAW DAMPER

ON

INOP

ON

INOP

ON

INOP

ANTI SKID

ON

ALTN

ON

ALTNELEC

L R

ENGCONT

ON

OFF

BAT

H

STBY POWER

OFFAUTO

BAT

0FF

DISCH

SQUELCH

OFFUSBAMF

ENG EECPRO BE

MA CHPRO BES

L T AT R T AT

L TAT

R AOAL AOA

PITOTR AUXPITOT

F O

PITOTL AUX

CAPTPITOT

R TAT

TOTAL A IR TEMP PROBES (2)



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 cir-

cuits.

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 cur-rent 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 con-dition, the current sensing relay, air/ground relay, and probe heat test relay sup-ply 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.

•



PROBE HEAT CIRCUIT

28V DC BAT BUS

R PROBE HT IND

P11

115V AC R BUS

AIR/TEST

TEST

R PROBE HT TEST (P33)

HEATER OFF

ADC

HEATER ON

F/O B PITOT PROBE HT

AIR/TEST

GND

115V AC R BUS

F/O A PITOT PROBE HT

P6

WING TAI/ WINDOW PROBE HT

TEST (P61)

F/O PITOT/ STATIC PROBE

N2 >50%

R PROBE HT N2 (P33)

N2 >50%

R N2 ENGINE SPEED CARD (P50)

N2 >50%

L N2 ENGINE SPEED CARD (P50)

GND

SYS 1 SYS 2 AIR/GND (P33) AIR/GND (P33)

10S NVM ON GND

L AND R EICAS CMPTR (E8-1)

F/O PITOT HEAT (M)

F/O P/S CURRENT SENSING (P33)

F/O MD&T PITOT

PROBE HT EICAS IND (C)

ANNUNCIATOR (P5)

PITOT HEAT LOW 115 VAC

AIRCRAFT ON GROUNDWITH ENGINES RUNNINGN2 > 50%



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.



ANGLE OF ATTACK PROBE HEATING (AOA)

115V AC R BUS

PROBE HT R AOA

P6

28V DC BAT BUS

RIGHT PROBE HT IND

P11

HEATER OFF

R AOA PROBE CUR SENSING (P33)

PROBE HEAT EICAS IND

ADC

MD&T

AIR/TEST

GND

SYS 2 AIR/GND

N2 >50%

R PROBE HT N2 (P33)

R AOA

VANE

CASE

R AOA SENSOR

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



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.



TOTAL AIR TEMPERATURE PROBE HEAT (TAT)

28V DC STBY BUS

LEFT PROBE HEAT IND

P11

115V AC L BUS

LEFT TAT PROBE HEAT

P6

HEATER OFF

AIR DATA/L C R

HEATER ON

TAT PROBE CURRENT SENSING

ENGINE AIR/TEST

SPEED

>50 PERCENT GND RPM

TAT PROBE HT SYS 2 AIR/GND

AIR/TEST

GND

SYS 1 AIR/GND

TAT PROBE

MD&T L TAT

ANNUNCIATOR

PROBE HEAT EICAS MESSAGE

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

Current Sense Relay OnlyOperates in AIR



WINDOW ANTI-ICEWINDOW HEAT CONTROL AND INDICATION

General

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.

Windows #2 & 3

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.

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



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



WINDOW HEAT CONTROL AND INDICATION (CONTINUED)

L WDO HT NO. 3

115V AC R BUS L WDO HT

NO. 2 ÷A

÷B

R WINDOW HT NO. 1

P37 PANEL

INOP

ON

W W

ON

A A

INOP

L SIDE CONTROL SW

INOP

ON

EICASINPUT L SIDE WINDOW

MASTER DIM ANDTEST

A

C

D

A

E

INTERNALS SAME AS

L FWD &

R SIDE WINDOW

HEAT CONT UNIT

J9

J12 COATING

C J10

CONT SNSR

RSV J11

TB 324 SPARE

1 L WINDOW 3

J8

COATING

D J7

CONT SNSR

RSV J6

TB 324 SPARE 1

L WINDOW 2

J1

J4

J5

INSTR LTS W W E EICAS INPUT

ON R FWDWINDOW B RSV

A A

B TB 324 INOP 1

R FWD CONTROL SW

WINDOW HEAT CONT PNL

COATING J3

CONT SNSR

J2

SPARE

R WINDOW 1

28V DC L BUS

WINDOW HEAT TEST

P11 PANEL

TB 324 AND TB323 FOR PICKING SPARE 1 SENSORS ARE LOCATED ON THE SIDES

OF THE E1 & E2 RACKS.

WINDOW HEAT L FWD & R SIDE

OFF

WINDOW/PROBE HEAT

WINDOW/PROBE HEAT SW R FWD & L SIDE WINDOW

MISC TEST PNL HEAT CONT UNIT

Window Heatis Divided and controlled:L Fwd and R Side Windows

And R Fwd and L Side Windows



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.


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.



WINDSHIELD WIPERS

MOTOR CONVERTER

WIPER ARM

ACCESS PANEL LIFT BLOCK WIPER BLADE IN

WINDSHIELD WIPER ASSEMBLY PARK POSITION

CONTROL PANEL

P5 PILOT'S OVERHEAD

PANEL

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



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



DRAIN MAST / AFT LINE HEATERS

(FUSELAGE)

(CEILING)

(FWD BULKHEAD)

FWD TRANSVERSE DRAIN

(MAIN DECK FLOOR)

THERMOSTAT

HEATER TAPE

(FUSELAGE)

FWD

DRAIN MAST

MID TRANSVERSE

DRAINS

(AFT

BULKHEAD)

AFT

TRANSVERSE DRAIN

(PRESSURE BULKHEAD)

AFT

DRAIN MAST

LEAD WIRES

CONTROL THERMOSTAT

WATER FILL CONNECTION THERMOSTAT

ELECTRICAL LEADS

WASTE TANK FITTING HEATER

DRAIN MAST EXTENSION TUBE HEATER TAPE

HEATER TAPE

DRAIN MAST

CONTROL THERMOSTATS

HEATING GASKET

HEATING GASKET LEAD

WATERLINE

RIBBON HEATER TAPE

TERMINAL BUTTON

ADHESIVETAPE

LEAD WIRES

WATER LINE HEATER TAPE WASTE TANK SERVICE PANEL



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).



WATER AND WASTE SYSTEM HEATERS

42.F (6.C)

115V AC

WATER LINE WATER LINE HTR TAPE HEATERS RELAY

40.F (4.C)

T

HTR TAPE CTRL THERMOSTAT

GASKET HTR

28V AC GND

115V AC AIR

SYS NO. 2

T

HTR TAPE W/CTRL THERMOSTAT

35.F (1.C)

T T

125.F (52.C)

WATER FILL FITTING HTR

35.F (1.C)

T T

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

WASTE TANK SVCE FITTING HTR

DRAIN MAST

AIR/GND RELAY

DRAIN MST HTR (EXAMPLE)

FORWARD DRAIN MAST

HEATING GASKET

B91 THERMOSTAT

WATER DRAIN SYSTEM

Documents

B767 ATA 30 Student Book