B767 ATA 33 Student Book

TRAINING MANUALFOR TRAINING PURPOSES ONLY

B767-3S2F ATA 33-00 Page - 1 1/2/13 EFF - ALL

CH 33

LIGHTING



TABLE OF CONTENTS

FLIGHT COMPARTMENT..................................................................... 4

PANEL DIMMER CONTROL UNITS ..................................................... 6

MASTER DIM AND TEST ..................................................................... 8

CARGO AND SERVICE LIGHTS ........................................................ 10

EXTERIOR ILLUMINATION ................................................................ 12

LOGO LIGHTS ................................................................................... 14



STUDENT NOTES:



FLIGHT COMPARTMENT LIGHTING

General

Flight compartment lighting is provided by incandescent dome lights in the ceiling panels and fluorescent lights over each crew member's instrument panel.

Integral Panel Lights

The instruments, annunciators, and systems control panels, have integral incandescent lights. The lights illuminate dials, annunciators, and switch position lettering.

Flight Compartment Miscellaneous Lights

Specific area lights such as map, chart, threshold stop, and flight kit lights are provided.

Master Dim and Test

A Master Dim and Test System allows the crew to dim and test all annunciator lights within the flight compartment.

Control

Lighting control panels at each crew member's station and overhead panel P5 allow the lights to be turned "ON", "OFF", and "DIMMED". Some control assemblies have dual functions. They have two potentiometers or rheostats. Each one is mounted on inner and outer knobs for control of integral panel lights and flood lights. The inner knob controls the flood lights and the outer knob controls the panel lights.



FLIGHT COMPARTMENT LIGHTING



PANEL DIMMER CONTROL UNITS

Panel/Flood Lights Dimmer Control Units

Panel/Flood Light Dimmer Control Units provide starting and dimming voltages for fluorescent and incandescent lights in the flight compartment. The units are on the forward end of the aisle stand under the P2 panel and outboard sides of the pilot's leg room areas.

The Dimmer Control Units for the aisle stand are in the aisle stand module and under the floor next to the aisle stand. The under floor units can be reached from the main equipment center.

Overhead Dimmer Control Units

The overhead panel (P5) and the circuit breaker panel (P11) light dimmer control units are attached to the drip shield on each side of the P5 panel and in the P11 circuit breaker panels.



PANEL DIMMER CONTROL UNITS



MASTER DIM AND TEST

General

The Master Dim and Test System controls all annunciators including those on the P61 panel. They are controlled with a rotary "DIM/BRT" switch and a push-button "TEST" switch on the overhead P5 panel. The "LT OVRD" switch on the P5 returns lighted annunciators to full brightness.

The annunciators use voltages from "TYPE I" dimmer control cards for dimming. These cards and associated master dim and test relays are in the lighting control panel P29 in the equipment center. Each card has a light emitting diode (LED) which lights when the card is operating properly. If the LED is off, the card is faulty. The cards provide a constant output regardless of the number of lights loading the circuit.

The auto-bright sensors in the P1-3 panel use photocells with amplifier circuits to sense ambient light condition. When the ambient light is low, the auto-bright sensor provides a ground to the auto-bright relays through a dimming relay contact, and removes the ground when the ambient light is bright inhibiting the dimming function.

The dim control relays are energized by the "DIM" position of the control switch providing a ground. When the equipment cooling system detects insufficient airflow or overheat ("OVHT" illuminates), a ground is removed from the power control relay. The relay then removes 28 volts dc from the dim control relays and disables the automatic dimming function. This ensures annunciation is visible to indicate overheat problems.

Positioning the rotary switch to "BRT" also removes the ground from the dim control relays and disconnects the autobright sensor outputs allowing the annunciators to go maximum brightness.

When the "TEST" switch is pressed, a ground is provided for test relays which completes 28 volt dc or a ground as applicable to all captain's and first officer's annunciation. The annunciators then light the brightness selected by the "DIM/BRT" switch. Faulty bulbs can then be observed and replaced as necessary.

The "TEST" switch also tests the electronic flight instrument system (EFIS) while on the ground. The switch should be held a minimum of 3 seconds (until the test patterns appear on the EADI and EHSI displays), to pre- vent blanking of the EFIS display units, which require resetting each of the Symbol Generators (SG). The switch is momentary on the -332 airplanes and latching on the -232 airplanes.

All primary 28 volt dc circuit breakers for Master Dim and Test Systems are on overhead circuit breaker panel P11. Secondary circuit breakers are on the P6 circuit breaker panel.



MASTER DIM AND TEST



CARGO AND SERVICE COMPARTMENT LIGHTS

General

Lighting is provided in the main and nose wheel wells, in the electrical/electronics compartments, and in the air conditioning, APU and tail cone compartments. Lighting is provided for the interior of the forward, aft and bulk cargo compartments.

Air Conditioning Bay Lighting

The air conditioning bay lights (left & right) are powered by the 115 volt ac Ground Handling Bus through a step-down transformer to 28 volts ac. The switches (S361 & S362) control two lights in the respective bay.

APU and Tail Cone Compartment Lighting

The APU compartment lights are powered by the 115 volt ac Ground Handling Bus. The power is transformed by a transformer (T149) from 115 volts ac to 28 volts ac. The APU compartment light switch (S428) controls the two lights. The tail cone compartment lights are controlled by two switches (S427 & S443).

Wheel Well Illumination

The nose wheel well incandescent lights are powered by the 28 volt ac Ground Service Bus. They are operated by a switch mounted on the P40 panel of the aft side of the nose landing gear. The main gear wheel well lights are powered by the 115 volt ac ground service bus which is converted to 28 volt ac by the wheel well lights transformer. Control is by two toggle switches wired in a two-way circuit. Switches are located in each wheel well on the keel beam.

Electrical/Electronics Compartments Illumination

The forward equipment center incandescent lamps are controlled by a toggle switch (S357) adjacent to the forward equipment center access door. Power comes from the 28 volt ac Ground Service Bus.

The main equipment center incandescent lamps are controlled by toggle switches wired in a three-way circuit. The switches are located adjacent to the Forward Cargo Compartment/Equipment Center Access Door (S354), the

Equipment Center Access Door (S355), and the equipment center access door in the cabin floor (S359). Power is from the 28 volt ac Ground Service Bus.

Cargo Compartments Illumination

The cargo compartments lighting consists of incandescent ceiling lights and a door mounted sill light. When the lens of each ceiling light fixture is removed, a micro-switch opens the light circuit.Power from the 115 volt ac Ground Handling Bus is applied to a transformer which provides 28 volt ac for all cargo lighting. Control of the lights in the forward cargo compartment is by a two-way circuit with toggle switches on the external (P43) and internal (P35) control panels, and by one set of contacts on the cargo door not closed relay. This relay is controlled by a proximity sensor in the door which provides a ground to enable the relay and the lights whenever the cargo door is not closed. The forward compartment lights are also controlled by a separate switch activated by opening the forward access door from the equipment center. This switch by-passes the two-way toggle switches and the door not closed relay circuit and turns on the lights.

The aft and bulk cargo compartment lights are controlled by three toggle switches. One switch is aft of the cargo door on the external (P44) control panel and one is in each doorway. The cargo lights enable relay is controlled by two proximity sensors which enable the lights when either door is open.



CARGO AND SERVICE LIGHTS



EXTERIOR ILLUMINATION

General

Airplane exterior lighting provides high intensity lights for identification of airplane position (navigation) and orientation. It also provides lighting for landing and taxi, and illuminating wing and engine areas. All lights are controlled from the flight compartment.

Wing/Engine Illumination Lights

Wing/Engine Illumination Lights are high intensity quartz halogen light assemblies on each side of the fuselage. A plano lens divides the light from a single lamp into two beams; one on the engine and one on the wing. A single on/off switch on the P5 panel controls both light assemblies.

Landing And Runway Turn-Off Lights

Two high intensity landing lights are on the nose landing gear. One high intensity landing light is in each wing root strakelet. Each wing light and the nose gear lights are controlled by separate on/off switches on the P5 panel. A landing gear lever position sensing switch changes the brightness of the wing landing lights from dim to bright when the landing gear lever is lowered. Another similar switch enables the nose gear landing lights when the gear is down and locked. Runway Turn-Off and Taxi lights are high intensity quartz halogen lights. The two taxi lights, mounted on the nose gear just below the landing lights, illuminates the ground ahead of the airplane. A runway Turn-Off Light in each wing root strake let illuminates the ground ahead and to the side of the airplane. Each light is controlled by a separate on/off switch on the P5 panel.

Position Lights

Quartz halogen position (navigation) lights in the leading and trailing edge of the wing-tips provides lighting for recognizing airplane position. Trailing edge lights are white. Left leading edge lights are red. Right leading edge lights are green. All lights are controlled by a single on/off switch on the P5 panel.

Anti-Collision Lights

Anti-Collision Lighting consists of two fuselage mounted strobe lights and two wing-tip mounted strobe lights. Fuselage lights are red and wing-tip lights are white. All lights are high intensity xenon strobe units which flash approximately 48 times per minute. White and red lights are controlled by separate alternate action switch-lights on the P5 panel.

Power for the fuselage mounted red lights comes from the 115 volt ac Ground Service Bus and is controlled by the "RED" anti-collision light switchlight. Wing-tip mounted white lights receive power from the 115 volt ac Left Bus and are controlled by the "WHITE" anti-collision switchlight. Both circuit breakers are located on the P11 circuit breaker panel.

The anti-collision light power supplies are located adjacent to each light. The power supply uses 115 volt ac applied through an internal fuse. Each power supply assembly contains transistorized power and timing circuits for flash tube operation. The timer and pulse generator produces a trigger pulse rate of 48+/-3 per minute. The high voltage (approximately 600 volts) pulse fires the xenon lamp which creates a conductive light.

WARNING: SINCE THE POWER SUPPLY UNIT CONTAINS HIGH VOLTAGE CIRCUITS, WAIT 10 MINUTES AFTER TURNING OFF POWER BEFORE DISCONNECTING CABLES OR OPENING UNITS. DO NOT ALLOW FINGERS TO TOUCH LAMPS. SKIN OILS MAY CAUSE THE LAMP TO DISCOLOR AND CRACK WHEN CURRENT IS APPLIED.



EXTERIOR ILLUMINATION



LOGO LIGHTS

General

Four logo lights are installed in the horizontal stabilizer and are positioned to illuminate the vertical stabilizer and rudder. They are controlled by a switchlight on the overhead panel.

Operation

Power to the logo lights is 115 volts ac from the ground service bus if the airplane is on the ground or from the right utility bus if the airplane is in flight. Each inboard logo light has an integral transformer to reduce the voltage to 12 volts ac. This transformer supplies power to both lights on the right or left horizontal stabilizer.

Maintenance Practices

Relamping is accomplished by removing 12 screws securing the lens assembly.

Note: The lens assembly is indexed and must be reinstalled in the correct position.

Pilot Emergency Lights Control Panel

The pilot's emergency lights control panel is located on the P5 panel. It consists of a guarded three-position (ON/ARMED/OFF) toggle switch and an "UNARMED" light. The switch controls all emergency lights, interior and exterior. In the "ARMED" position, all emergency lights come on automatically when electrical power is lost. The indicator light annunciates "UNARMED" when the switch is not in the "ARMED" position.



LOGO LIGHTS

Documents

B767 ATA 33 Student Book