B767 ATA 26 Student Book

FIRE PROTECTION ATA 26

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ATA 26 FIRE PROTECTION TABLE OF CONTENTS......................................................................... 1 FIRE PROTECTION - INTRODUCTION ............................................... 2 FIRE PROTECTION - OPERATIONAL TEST ....................................... 4 FIRE DETECTION SYSTEM ................................................................. 6 ENGINE/FIRE OVERHEAT DETECTION TEST FIRE.......................... 8 ENGINE FIRE OVRHEAT DETECTION - INTRO ............................... 12 GENERAL DESCRIPTION .................................................................. 14 MAIN DECK CARGO SMOKE DETECTION SYSTEM - GEN DESC . 26 FREIGHTER LAV SMOKE DETECTION GENERAL DESC ............... 28 APU FIRE DETECTION - INTRODUCTION & LOCATION................. 36 GENERAL DESCRIPTION .................................................................. 38 APU FIRE DETECTION - INDICATIONS ............................................ 44 LWR CARGO COMP SMOKE DETECTION - INTRODUCTION......... 48 LWR CARGO COMP- SMOKE DET - FUNCTIONAL DESCRIPTION 56 AFOLTS CARD - FUNCTIONAL DESCRIPTION - DUAL LOOP ........ 62 WHEEL WELL FIRE DETECTION - INTRODUCTION ....................... 64 WING AND BODY DUCT LEAK DETECTION & INTRODUCTION .... 70 STRUT OVERHEAT DETECTORS - FUNCTIONAL DESCRIPTION . 76 ENGINE FIRE EXTINGUISHING - COMPONENT LOCATIONS ........ 80 APU FIRE EXTINGUISHING - INTRODUCTION ................................ 96 LOWER CARGO FIRE EXTINGUISHING - INTRODUCTION .......... 106

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FIRE PROTECTION - INTRODUCTION Purpose The fire protection systems monitor the airplane for these conditions: • • • • •

Fire Smoke Engine overheat Pneumatic duct leak Strut leak detection

The fire protection systems also include fire extinguishers. Fire/Overheat Detection The airplane has these fire/overheat detection systems: • • • • • • • •

Engine fire detection Engine overheat detection APU fire detection Cargo compartment smoke detection Wheel Well fire detection Duct leak detection Lavatory smoke detection Electrical and electronic (E/E) cooling smoke detection

Extinguishing • • • • • •

The airplane has these fire extinguishing systems: Engine APU Cargo compartment Lavatory Portable fire extinguishers

Abbreviations and Acronyms A/G AFOLTS

- air ground system - automatic fire overheat logic test system

APU APUC ARINC auto BIT BITE btl btls cgo ch disch DLODS ECS EDP EEC EICAS ENG equip ext fwd ind kg LED LRU MD&T MEC ovht ovrd press PSEU pwr rmt stby vlv WEU WOW

-

auxiliary power unit auxiliary power unit controller Aeronautical Radio, Inc. automatic built-in-test built-in-test-equipment bottle bottles cargo channel discharge duct leak and overheat detection system environmental control system engine-driven pump electronic engine controller engine indication and crew alerting system engine equipment extinguishing forward indicator kilogram light emitting diode line replaceable unit master dim and test main equipment center overheat override pressure proximity switch electronics unit power remote standby valve warning electronics unit weight-on-wheels

FIRE/OVHT PROTECTION

ENGINE SYSTEMS - FIRE - OVHT - EXTINGUISHING

APU SYSTEM - FIRE - EXTINGUISHING

CARGO SYSTEMS - FIRE - EXTINGUISHING

WHEEL WELL SYSTEM - FIRE

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DUCT LEAK SYSTEM - OVHT

LAVATORY - FIRE/SMOKE - EXTINGUISHING

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FIRE DETECTION SYSTEM

Cargo Smoke Detection System

Engine Fire

The forward and aft cargo compartments contain two smoke detectors in each compartment. When a preset level of smoke is detected by both detectors(AND logic), the number six AFOLTS card outputs a cargo fire signal. The smoke detectors use a vacuum system to generate a blow through sample of compartment air for increased reliability.

The left and right engine systems are identical. Each engine has a dual loop detector system. The engine fire loops are broken into three separate elements; the engine accessory area, the upper turbine area, and the lower turbine area. These detector loops send signals of a fire or fault condition to its interchangeable dedicated detector card. These detector cards are located in the P54 fire detection card file in the main equipment center. The detector cards discriminate between fire and fault conditions and send that message to the automatic fire/overheat logic/test system card (AFOLTS card) also located in the P54 file. If the programmed logic in AFOLTS is satisfied (AND logic when configured in dual loop), the AFOLTS card alerts the flight crew. Some of the flight compartment outputs are shown. Engine Overheat The overheat system is a very similar system to the engine fire system. The major differences are that only one segment is located on the engine, at the pneumatic ducting area, and that an overheat is a caution not a warning. AFOLTS card No. 1 is shared by left engine fire and left engine overheat, while the right engine uses AFOLTS card No. 2. All AFOLTS cards are interchangeable. APU Fire The APU dual detector loop system protects against APU compartment fires. There are two segments, one located above the APU on the air intake and one located below the APU on the clam shell door. The loops feed their detector cards (identical to the engine detector cards). The APU detector cards feed AFOLTS card No. 3. The flight compartment outputs are shown. Wheel Well Fire and Duct Leak Detection A single loop wheel well fire system is wired in series through both wheel wells into one detection segment. The Fenwal built system feeds the wheel well fire/ duct leak detection card. This unique card is also in the P54 card file. Outputs from this card feed the wheel well fire indicators in the flight compartment. A wheel well fire is a warning alert. The three duct leak zones; left wing, right wing, and body, also feed the wheel well fire/duct leak detection card.

Testing The ENG/APU/CARGO test switch on the test panel sends an input to all AFOLTS cards to run a circuit check of the detector cards and a continuity check of the loops that feed them. If the cards and loops are working correctly, the AFOLTS cards will output fire and overheat signals to the flight compartment. If one loop fails, the test is still successful but the bad loop is annunciated on EICAS. If both loops fail, the test is unsuccessful and the test panel fail light illuminates. The wheel well test switch runs a continuity check of the wheel well detector loop. The duct leak continuity test is initiated at the P61 duct leak panel. If the duct leak lights illuminate, the system is continuous.

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ENGINE FIRE OVERHEAT DETECTION - GENERAL DESCRIPTION General Each engine has two fire detection loops. A fire detection card in the system card file monitors the loops for fires, overheat conditions, and faults. There is a fire detection card for each engine. Overheat Detection If the fire detection loops find an overheat condition, the fire detection card sends a signal to the AFOLTS card and to the warning electronics unit. The AFOLTS card sends a caution message and turns on the master caution light. The warning electronics unit turns on the master caution light and overheat aural warning. When the overheat condition goes away, the indications go away. Fire Detection If there is an engine fire, the detection loop sends a signal to the fire detection card. The detection card sends a signal to the AFOLTS card. The AFOLTS card sends signals to the warning electronics unit and to flight deck indications. When the fire is out, the indications go away. Continuous Fault Monitoring The fire detection card monitors the two loops and the wiring for defects. In normal (dual loop) operation, both loops must have a fire or overheat to cause the flight deck indications. If a failure occurs in a loop, the fire detection card sends the data to AFOLTS. A status message shows. The system changes to single loop operation with the FIRE/OVHT TEST switch on the P8 panel. In this mode, fire and overheat indications occur when one loop is defective and the other has a fire or overheat condition.

System Tests Use the FIRE/OVERHEAT test switch on the P8 panel to do a test of the system. Test indications are the same as the actual fire and overheat warning indications.

FIRE FIRE LIGHT

R OVHT DET CARD LOOP 2

R NACELLE OVHT DET LOOP 2

R OVHT DET CARD LOOP 1

R NACELLE OVHT DET LOOP 1

R FIRE DET CARD LOOP 2

R ENGINE FIRE DET LOOP 2

R FIRE DET CARD LOOP 1

R ENGINE FIRE DET LOOP 1

L FIRE DET CARD LOOP 1

L ENGINE FIRE DET LOOP 1

L FIRE DET CARD LOOP 2

L ENGINE FIRE DET LOOP 2

L OVHT DET CARD LOOP 1

L NACELLE OVHT DET LOOP 1

L OVHT DET CARD LOOP 2

L NACELLE OVHT DET LOOP 2

L ENG OVHT

ENG BTL 1 DISCH

ENG BTL 2 DISCH

R ENG OVHT

DISCH

AFOLTS CARD 2

1

1

2

L E F T

DISCH 2

R I G H T

ENGINE FIRE CONTROL PANEL

FIRE, OVHT AND FAULT INDICATIONS AND TEST CIRCUITS

AFOLTS CARD 1

FIRE/OVHT TEST WHL WELL

ENGINE FIRE OVERHEAT DETECTION - GENERAL DESCRIPTION Page - 7

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SYS FAIL

FAIL P-RESET

FIRE TEST PANEL

P54 FIRE DET CARD FILE

B767-3S2F

ENG/APU CARGO

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ENGINE FIRE OVERHEAT DETECTION - INTRODUCTION Purpose The engine fire/overheat detection system has these functions: • Gives warnings in the flight compartment if there is a fire in an engine nacelle • Gives caution indications in the flight compartment if an engine has an overheat condition • Does tests on the system • Changes system operation in relation to pass/fail status of detector loops • Gives flight compartment messages for system condition

DUAL LOOP ENGINE FIRE AND OVERHEAT DETECTORS ENGINE FIRE OVERHEAT DETECTION - INTRODUCTION B767-3S2F Page - 9

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FLIGHT DECK INDICATIONS - INTRODUCTIONS Functional Description A fire in the engine will display the following indications: • • • • • •

Discrete warning display Master warning light Fuel control switch Engine fire handle Fire bell EICAS warning message


WARNING CAUTION

WARNING

AURAL INDICATION SPEAKERS (WARNING & CAUTION)

P7

FIRE

CONFIG

PULL UP

A/P DISC

CAUTION

P7

L-

FUEL CONTROL

-R

RUN

CABIN OVSPD ALT DISCRETE WARNING DISPLAY (P1-3)

CUT OFF FUEL CONTROL SWITCH MODULE (P10)

L ENG FIRE L ENG OVHT

ENG BTL 1 DISCH

ENG BTL 2 DISCH

R ENG OVHT

DISCH 1

FIRE CONTROL PANEL (P8)

EICAS DISPLAY UNITS (P2)

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L E F T

L ENG FIRE LP 1 L ENG FIRE LP 2

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DISCH 2

R I G H T

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ENGINE FIRE DETECTION - FIRE DETECTORS Purpose The engine fire/overheat detection system monitors the engine for fire or overheat conditions. Physical Description The engine fire/overheat detection system has these components: • • • •

Lower forward engine detector Lower aft engine detector Upper aft (firewall) detector Forward upper overheat detector

Location The lower forward detector is below the engine fan section. The lower aft detector is below the turbine section of the engine. The upper aft (firewall) detector is above the turbine section of the engine. The overheat detector is in the strut area of the engine.

UPPER FWD ENGINE OVERHEAT DETECTOR

UPPER AFT ENGINE FIREWALL FIRE DETECTOR

LOWER AFT ENGINE FIRE DETECTOR

LOWER FORWARD ENGINE FIRE DETECTOR

SENSOR ELEMENT

SUPPORT TUBE

ENGINE FIRE DETECTION SENSOR (TYPICAL) ENGINE FIRE DETECTION - FIRE DETECTORS B767-3S2F Page - 13

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ATTACHMENT LUG

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ENGINE FIRE DETECTORS - FUNCTIONAL DESCRIPTION Physical Description Two sensing elements are parallel on either side of a contoured rigid support tube. These elements have an tube with thermistor material with two embedded electrical conductors. Both ends of the tube are electrical connectors attached to the conductors with one of the conductors grounded to the shell of the connector. Functional Description When the overheat sensor loop gets to the trip temperature, the thermistor material in the tubing decreases in resistance and sends an overheat signal to the fire detector card. When the LOWER FORWARD, LOWER AFT, and UPPER AFT fire detection sensors get to the trip temperatures, the thermistor material has decreased its resistance to the trip point and sends a fire signal to the fire detector card. The fire detector sensors and overheat sensors have a discrete trip temperature for localized hot spots. The sensors reset when the temperature cools sufficiently. The environmental temperature is provided to help determine the operating temperature and a guide to the capability of resetting the sensor.

UPPER AFT ENGINE FIREWALL FIRE DETECTOR

UPPER FWD ENGINE OVERHEAT DETECTOR

LOWER FORWARD ENGINE FIRE DETECTOR

LOWER AFT ENGINE FIRE DETECTOR ENGINE FIRE DETECTION SENSOR (TYPICAL)

TRIP TEMPERATURES

ENVIRONMENTAL RESET TEMPERATURE TEMPERATURE

LOCATION

1

TOTAL LENGTH (AVERAGE) 1

ONE FOOT DISCRETE (MAXIMUM)

(MINIMUM)

(MAXIMUM)

UPPER FWD (OVERHEAT)

600F

950F

500F

485F

LOWER FORWARD

750F

1050F

400F

250F

LOWER AFT

750F

1100F

650F

500F

UPPER AFT

800F

1150F

700F

700F

TOLERANCE ALLOWANCE IS 50F

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AFOLTS CARDS - FUNCTIONAL DESCRIPTION - DUAL LOOP General The automatic fire and overheat logic and test system (AFOLTS) cards give indications of fire or overheat conditions when the detector cards receive alarm or fault signals from the fire or overheat detection loops. Outputs from the AFOLTS card give indications and flight compartment messages. The cards can operate in dual loop mode (normal) or single loop mode. The dual loop mode shows here. An AFOLTS card receives alarm and fault signals from four detector cards. The detector cards connect to two fire detection loops and to two overheat detection loops. During dual loop mode operation, an alarm or fault signal is necessary from the two detector cards to make an alarm warning of a fire or overheat condition. EICAS A single loop output shows as a message on the status and maintenance pages. If the two loops have an output (alarm), the EICAS display changes to a warning, and the loop messages are disabled. Test When the card is in the dual loop mode, it monitors loop 1 and loop 2 detector cards. If the detector card finds a fault with one or two of its loops during a power-up self-test or a manual test from the P8 panel, a fault signal goes to the AFOLTS card and the AFOLTS sends status and maintenance messages to the flight deck to show which loop has a failure. If there is a failure of one loop, the AFOLTS card ignores that loop, and the system operates in the single loop mode with different logic. If the two loops have failures, a SYS FAIL light and FIRE/OVHT SYS advisory message shows in the flight compartment. Detector, card, or related wiring failures cannot give a valid fault output at the moment of a failure. These defective loops can only be found during a system test.

Automatic 60 Minute Test The AFOLTS card automatically gives a self test command to the detection zones when the detection loops, fire/overheat/smoke, in a zone are in disagreement for more than five seconds, or the zone is already in the single loop mode. The AFOLTS card gives the self test command every 60 minutes if the initial condition does not change or stays in the single loop operation.

LOOP MSG(S&M)

SYS FAIL LIGHT

EICAS LOOP 1 FIRE/OVHT SYS

ENG/APU/CARGO TEST SWITCH

LOOP MSG(S&M)

FIRE/OVHT TEST PANEL (P8) ALARM TEST

TEST SEQUENCER

L EICAS COMPUTER

FAULT TEST

LOOP MSG(S&M)

ALARM TEST

T

EICAS LOOP 2

FIRE/OVHT SYS

FAULT TEST

LOOP 1 DETECTOR CARD

T

LOOP 2 DETECTOR CARD

2

SOFTWARE FAULT ALARM

P54

FAULT ALARM

2

ALARM + ALARM = ALARM ALARM + FAULT = ALARM

ALARM 1 ALARM 2

FAULT + ALARM = ALARM FAULT + FAULT = FAIL LIGHT ALARM OR FAULT + NOTHING FOR MORE THAN 5 SEC = TEST EVERY 60 MINUTES.

STARTS BY NOSE STRUT EXTENSION ON TAKEOFF CIRCUIT INOPERATIVE SIGNAL AS FOUND BY A FAILED TEST

MASTER WARN NOT PUSHED RADIO ALTM <400 FEET

<20 SEC AFTER TAKEOFF 1 NOTE: STATUS LOOP MSGS ARE INHIBITED DURING AN ALARM.MAINTENANCE LOOP MSGS ARE SHOWN DURING AN ALARM. WARNING ELECTRONICS UNIT (P51)

AFOLTS CARDS - FUNCTIONAL DESCRIPTION - DUAL LOOP B767-3S2F Page - 17

R EICAS COMPUTER 1. FIRE DISCRETE ANN (P1-3) 1. FIRE SW LIGHTS (P8) 2. FIRE SW LOCK RELEASE (P8) 3. FUEL CONT SW LIGHT (P8)

AFOLTS (TYP) (P54)

P54 1

LOOP MSG(S&M)

2

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1. MASTER WARNING LIGHTS (P7) 2. FIRE WARNING BELL

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AFOLTS CARDS - FUNCTIONAL DESCRIPTION - SINGLE LOOP General The automatic fire/overheat logic test system (AFOLTS) can operate in either a dual loop mode or a single loop mode. The single loop mode is shown here. The AFOLTS card can deselect a faulty detection loop after that loop has failed a test. The test may be either a self-test started when power is applied to the battery bus (or when power is interrupted for more than two milliseconds) or a manual test from the P8 panel. After an AFOLTS card deselects a faulty loop, the fire/overheat detection system only needs a single alarm or fault signal from the remaining good loop. If a fire or overheat condition is detected in the single loop mode, flight deck warning and indications are the same as for the dual loop mode.

LOOP 1 AFOLTS CONFIG ALARM

LOOP 2

FAULT

ALARM

INDICATION

FAULT

X X

SINGLE LOOP MODE

DESELECTED BY AFOLTS

DESELECTED BY AFOLTS

X

FIRE -OROVHT X

X X

STATUS AND MAINTENANCE MESSAGES X

2

X

1

X

2

X

1

AFOLTS CARD - LOGIC TABLE FOR SINGLE LOOP CONFIGURATION

1

SYS FAIL LIGHT AND FIRE/OVHT SYS ADVISORY MESSAGE SHOWN ON FLIGHT DECK.

2

STATUS LOOP MESSAGES ARE INHIBITED DURING AN ALARM. MAINTENANCE LOOP MESSAGES ARE SHOW.

AFOLTS CARDS - FUNCTIONAL DESCRIPTION - SINGLE LOOP B767-3S2F Page - 19

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ENGINE/FIRE OVERHEAT DETECTION - INDICATIONS Fire Indication If there is an engine fire, these are the indications in the flight compartment: • • • • • • •

Fire switch light Fire switch lock releases Fuel control switch light EICAS warning message, L (R) ENGINE FIRE Discrete fire warning light Flight compartment fire bell Master warning lights

Overheat Indication If an engine has an overheat, these are the indications: • • • •

Discrete overheat annunciator light EICAS caution message, L (R) ENG OVHT Caution aural Master caution lights

WARNING

WARNING

CAUTION

CAUTION

P7

FIRE

CONFIG

PULL UP

A/P DISC

P7

L

FUEL CONTROL

R

RUN


CUT OFF FUEL CONTROL SWITCH MODULE (P10)

L ENG FIRE L ENG OVHT L ENG OVHT

ENG BTL 1 DISCH

DISCH


1

L ENG OVHT LP 1 L ENG OVHT LP 2

AURAL WARNING SPEAKERS (WARNING & CAUTION)

2

L E F T

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ENG BTL 2 DISCH

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R ENG OVHT

DISCH 2

R I G H T

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ENGINE/FIRE OVERHEAT DETECTION - TEST FIRE General The fire test switch (ENG/APU/CARGO) does a test of these systems: • Engine fire/overheat detection • APU fire detection • Cargo smoke detection Only the engine fire detection test is shown here. Fire Test Indications When you push the ENG/APU/CARGO test switch, these indications come on: • • • • • •

Fire switch Fuel control switch Discrete fire warning light Master warning lights Flight compartment fire bell Flight deck warning, status, and maintenance messages

Test Initiation The test is started with the FIRE/OVHT TEST - ENG/APU/CARGO switch on the P8 panel. The complete test takes four seconds. During this time, all the engine fire detector loops show as flight deck messages. Fire Test Pass When you release the switch, all test indications go away. The systems may have faults which do not prevent flight. An example is a single loop fault in the engine fire detection system. A status message shows this fault. Refer to the Dispatch Deviation Guide to see if this fault will limit flight operations. Fire Test Fail When you release the switch, any faulty loops show on the EICAS status and maintenance pages. If one loop of the left engine fire detection system fails, for

example, that loop is deselected and the system changes to a single loop configuration using the input from the remaining good loop. If both left engine fire detection loops fail, the SYS FAIL light on the P8 test module comes on and the EICAS advisory message, FIRE/OVHT SYS shows. Push the fail light to turn off the light and remove the EICAS advisory message.

AURAL WARNING SPEAKER

WARNING

FIRE/OVHT TEST R

WHL WELL

A/P DISC

ENG BTL 2 DISCH

ENG BTL 1 DISCH

DISCH 2

DISCH 1

OVSPD

1

2

R ENG OVHT

R I G H T

L E F T

ENGINE FIRE CONTROL PANEL (P8)

SYS FAIL

ENG/APU CARGO FAIL P-RESET

CUT OFF

CENTER QUADRANT (P10)

PULL UP

L ENG OVHT

DISCRETE WARNING DISPLAY (P1-3)

P7

FUEL CONTROL RUN

CONFIG

CABIN ALT

CAUTION

L

FIRE

TAT + 12C

AFT CONTROL STAND (P8)

+10c D-TO

REV TAI

54.2

21.3

109.7

L ENG FIRE

ALARM WARNING SIGNAL 2 SYSTEM MANUAL TEST ENG FIREWALL FIRE DET

ALARM WARN SIGNAL 1

N

FIRE/OVHT SYS

DUAL LOOP FAULT SIGNAL

1

HOT

825

528

826 EGT

LOOP 1 AND 2 ALARM/FAULT SIGNALS

ECS/MAINT

LOOP 1 DET SIG LOOP 2 DET SIG

1

LWR AFT ENG FIRE DET

L(R) EICAS COMPUTERS (E8)

LWR FWD ENG FIRE DET 1

SHOWS WHILE TEST SWITCH IS PUSHED FOR LOOP TEST, LIGHT GOES OUT WHEN SWITCH IS RELEASED IF THE LOOP TEST IS SUCCESSFUL

FIRE DETECTION CARD FILE (P54)

WARNING ELECTRONICS UNIT (P51)

ENGINE/FIRE OVERHEAT DETECTION - TEST FIRE B767-3S2F Page - 23

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ENGINE FIRE/OVERHEAT DETECTION - TEST OVERHEAT General The fire test switch (ENG/APU/CARGO) does a test of these systems: • Engine fire/overheat detection • APU fire detection • Cargo smoke detection Only the engine overheat detection test is shown here. Overheat Test Indications When you push the ENG/APU/CARGO test switch, these indications come on: • Master caution lights • Caution aural tone • Flight deck caution, status, and maintenance messages Test Initiation The test is started with the FIRE/OVHT TEST - ENG/APU/CARGO switch on the P8 panel. The test takes four seconds. During this time, all the engine overheat detector loops show as flight deck messages. Overheat Test Pass When you release the switch, all test indications go away. The systems may have faults which do not prevent flight. An example is a single loop fault in the engine overheat detection system. A status message shows this fault. Refer to the Dispatch Deviation Guide to see if this fault will limit flight operations. Overheat Test Fail When you release the switch, any faulty loops show on the EICAS status and maintenance pages. If one loop of the left engine overheat detection system fails, for example, that loop is deselected and the system changes to a single loop configuration using the input from the remaining good loop. If both left engine overheat detection loops fail, the SYS FAIL light on the P8 test module

comes on and the EICAS advisory message, FIRE/OVHT SYS shows. Push the fail light to turn off the light and remove the EICAS advisory message.

UPPER FWD ENG OVHT DET

AURAL WARN SPEAKERS (CAUTION)

ENG BTL 1 DISCH

L ENG OVHT

ENG BTL 2 DISCH

DISCH 1

SYS FAIL

CAUTION

ENG/APU CARGO

WHL WELL

P7

DISCH 2

L E F T

WARNING FIRE/OVHT TEST

1

2

R ENG OVHT

R I G H T

ENGINE FIRE CONTROL PANEL (P8)

FAIL P-RESET TAT + 12C

+10c D-TO

REV TAI

AFT CONTROL STAND (P8) SYSTEM MANUAL TEST

54.2

21.3

109.7

ALARM SIGNAL

L ENG FIRE N

FIRE/OVHT SYS


1

HOT

825

528

826 EGT

LOOP 1 DETECTOR LOOP 2 DETECTOR

LOOP 1 & 2 ALARM/FAULT SIGNALS

ECS/MAINT

1 FIRE DETECTION CARD FILE (P54) 1


SHOWS WHILE TEST SWITCH IS PUSHED DURING LOOP TEST, REMOVED WHEN SWITCH IS RELEASED IF THE LOOP TEST IS SUCCESSFUL

L (R) EICAS COMPUTERS (E8) EICAS DISPLAY UNITS (P2)

ENGINE FIRE/OVERHEAT DETECTION - TEST OVERHEAT B767-3S2F Page - 25

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L ENG OVHT LP 1 L ENG OVHT LP 2


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ENGINE FIRE EXTINGUISHING - INTRODUCTION Purpose The engine fire extinguishing system extinguishes fires in the engine nacelles. General Description The two fire extinguishing bottles contain halon fire extinguishing agent pressurized with nitrogen. You use the engine fire switches in the flight deck to release the halon. Halon from each bottle can go to the left or right engine. EICAS messages, status messages, and indicator lights show when the bottle pressure is low.

ENG BTL 1 DISCH

ENG BTL 2 DISCH

DISCH 1 2

DISCH 1

2

R I G H T

L E F T

1

2


FWD CARGO COMPARTMENT DISTRIBUTION TUBE

ENGINE FIRE EXTINGUISHING - INTRODUCTION B767-3S2F Page - 27

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ENGINE FIRE EXTINGUISHING - COMPONENT LOCATIONS Purpose The engine fire extinguishing system extinguishes fires in the engine nacelles. General Description The two fire extinguishing bottles contain halon fire extinguishing agent pressurized with nitrogen. You use the engine fire switches in the flight deck to release the halon. Halon from each bottle can go to the left or right engine. EICAS messages, status messages, and indicator lights show when the bottle pressure is low. Flight Deck Component Locations The engine fire panel is in the flight deck on the P8 aisle stand. Forward Cargo Compartment Component locations The two engine fire extinguishing bottles are behind the right sidewall lining of the cargo door. Open the cargo compartment lining to get access to the bottles.

ENG BTL 1 DISCH

ENG BTL 2 DISCH

DISCH 1

2

1

L E F T

DISCH 2

R I G H T


1

2 1

2

FWD CARGO COMPARTMENT DISTRIBUTION TUBE

CARGO SIDEWALL

ENGINE FIRE BOTTLES

ENGINE FIRE EXTINGUISHING - COMPONENT LOCATIONS B767-3S2F Page - 29

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FWD CARGO BAY FLOOR

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ENGINE FIRE EXTINGUISHING - BOTTLES

Training Information Point

Purpose

When you replace bottles, handle them carefully to prevent damage. Compare the weight of the new bottle with the weight on the identification plate. This prevents installation of a bottle which is not full.

The engine fire extinguishing bottles contain the fire extinguishing agent. Location

The discharge ports of the bottle for the left and right engines are different sizes and are also color coded. This prevents crossed connections.

The engine fire extinguishing bottles are outboard of the right sidewall lining of the forward cargo compartment in the right rear corner.

WARNING: BE CAREFUL WHEN YOU MOVE THE FIRE

Physical Description The two engine fire extinguishing bottles are identical. Each bottle has these components: • • • • •

Safety relief and fill port Low pressure switch Two discharge assemblies Switch test push button Four mounting lugs

The engine fire extinguishing bottles are interchangeable with the APU fire extinguishing bottle.

EXTINGUISHING BOTTLE. THE FIRE EXTINGUISHING BOTTLE IS HIGHLY PRESSURIZED AND HAS AN EXPLOSIVE CARTRIDGE AS A COMPONENT. ACCIDENTAL DISCHARGE OF THE FIRE EXTINGUISHING BOTTLE CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMEMT.

WARNING: DO NOT TOUCH THE SQUIB BEFORE YOU DO THE PROCEDURES FOR DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE THE FIRE BOTTLE TO RELEASE ITS CONTENTS SUDDENLY AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

WARNING: PUT A PROTECTIVE COVER ON THE SQUIB. IF YOU DO Functional Description The bottles contain 19 pounds of halon fire extinguishing agent pressurized to 825 psi with nitrogen. If the pressure in the bottle becomes too high, the safety relief and fill port opens so the bottle does not explode. The discharge assembly has an explosive squib. An electric current from the fire extinguishing circuit fires the squib. This releases the halon through the discharge port. The pressure switch gives flight deck indications when bottle pressure decreases. The switch monitors the pressure in the bottle and is normally open. When the pressure decreases because of a leak or because of bottle discharge, the switch closes and causes the EICAS message.

NOT PUT A PROTECTIVE COVER ON THE SQUIB, THE FIRE EXTINGUISHING BOTTLE CAN RELEASE ITS CONTENTS SUDDENLY AND CAUSE INJURY TO PERSONS.

LOW PRESSURE SW (375 PSI)

SAFETY RELIEF AND FILLER PORT (1925 PSI)

SWITCH TEST PUSH BUTTON

MOUNTING LUG (4)

RIGHT ENGINE DISCHARGE PORT PORT (1 INCH)

L SQUIB GROUND WIRE LEFT ENGINE DISCHARGE PORT (1-1/4 INCH)

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ENGINE FIRE BOTTLE (TYPICAL) ENGINE FIRE EXTINGUISHING - BOTTLES


R SQUIB

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ENGINE FIRE EXTINGUISHING - BOTTLE/SQUIBS Purpose The squib releases the halon from the engine fire extinguishing bottle. Location The squib is in the discharge assembly at the bottom of the fire bottle. Each fire bottle has two squibs, one for each engine. Physical Description The squib is an electrically operated explosive device. The squib is adjacent to a bottle diaphragm that can break. The diaphragm normally seals the pressurized bottle. Functional Description The squib fires when you put the fire switch to the DISCH 1 or DISCH 2 position. The explosion opens the diaphragm. Nitrogen pressure in the bottle pushes the halon through the discharge port. Training Information Point You use the SQUIB TEST PANEL (P61) to do a squib test. See the fire protection section for more information about the squib tests.

WARNING: MAKE SURE THERE IS NO VOLTAGE AT THE ELECTRICAL CONNECTOR. IF THERE IS A VOLTAGE AT THE ELECTRICAL CONNECTOR, THE SQUIB CAN ACCIDENTALLY FIRE AND CAUSE THE FIRE EXTINGUISHING BOTTLE TO RELEASE ITS CONTENTS. ACCIDENTAL DISCHARGE OF THE FIRE EXTINGUISHING BOTTLE CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

WARNING: PUT A PROTECTIVE COVER ON THE SQUIB. IF YOU DO NOT PUT A PROTECTIVE COVER ON THE SQUIB, THE FIRE EXTINGUISHING BOTTLE CAN RELEASE ITS

CONTENTS SUDDENLY AND CAUSE INJURY TO PERSONS. CAUTION: DO NOT PUT A SHUNT PLUG ON THE SQUIB. THE SHUNT PLUG CAN CAUSE DAMAGE TO THE SQUIB PINS. The electrical connectors and the discharge assembly interface threads are different sizes and colors for the left and right engine squibs. This prevents an incorrect connection.

DIAPHRAGM

BOTTLE (REF)

GLAND NUT

DISCHARGE PORT

DISCHARGE ASSEMBLY SQUIB GROUND LUG ELECTRICAL CONNECTOR LEFT SQUIB

SQUIB ASSEMBLY (TYPICAL)

RIGHT SQUIB

ENGINE FIRE EXTINGUISHING - BOTTLE/SQUIBS B767-3S2F Page - 33

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ENGINE FIRE EXTINGUISHING - ENGINE FIRE PANEL Purpose The engine fire switches and engine fire bottle discharge lights are on the engine fire panel in easy reach of the flight crew. Location The engine fire panel is in the flight deck on the P8 aisle stand. Physical Description The engine fire panel has a fire switch for each engine and a discharge light for each fire bottle. Quick release fasteners attach the panel to the aisle stand structure. Electrical connectors connect the panel to the airplane wiring.

ENGINE BOTTLE DISCHARGE LIGHTS QUICK RELEASE FASTENER (4)

ENGINE FIRE WARN LIGHT ELECTRICAL CONNECTOR

ENGINE FIRE PANEL ENGINE FIRE OVERRIDE SW ENGINE FIRE SW

ENGINE FIRE EXTINGUISHING - ENGINE FIRE PANEL B767-3S2F Page - 35

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ENGINE FIRE EXTINGUISHING - ENGINE FIRE SWITCH

You must put the switch back to the center position before you can push the switch in.

Purpose


The engine fire switch does these four things:

The left engine and right engine fire switches are interchangeable.

• • • •

Gives an indication of an engine fire Stops the engine Isolates the engine from the airplane systems Controls the engine fire extinguishing system

Physical Description The engine fire switch includes these parts: • • • • • •

Engine fire warning light Solenoid Engine fire override button Push-pull switch contacts (internal) Rotary switch contacts (internal) Electrical connector

Functional Description The solenoid locks the fire switch, so you cannot pull it accidently. If an engine has a fire, the fire warning light comes on, and the solenoid energizes to release the switch. The fire override button lets you pull the fire switch when the solenoid is not energized. When you pull the fire switch, the push-pull switch contacts operate electrical circuits that stop the engine and isolate it from the airplane systems. When you pull the switch, you can turn it left or right to a mechanical stop at the discharge position. The rotary switch contacts close and operate the fire extinguishing system. When you release the switch, a spring moves the switch a small distance from the discharge position to open the switch contacts.

When operating the fire switches in the discharge position, make sure that the fire bottle discharge light illuminates.

ENGINE FIRE WARNING LIGHT

ENGINE FIRE OVERRIDE BUTTON

CENTER SPRING RETURN (SWITCH OPEN)

PUSH-PULL CONTACTS (INTERNAL)

DISCH 1

DISCHARGE 1 (SWITCH CLOSED)

2

SPRING RETURN (SWITCH OPEN)

L E F T

ROTARY CONTACTS (INTERNAL)

ELECTRICAL CONNECTOR

DISCHARGE 2 (SWITCH CLOSED)

SWITCH POSITIONS

ENGINE FIRE SWITCH (P8) ENGINE FIRE OVERRIDE BUTTON PUSHED

SOLENOID ENERGIZED

SWITCH LOCKED

SWITCH RELEASED ELECTRICALLY

SWITCH RELEASED MANUALLY

ENGINE FIRE EXTINGUISHING - ENGINE FIRE SWITCH B767-3S2F Page - 37

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SWITCH PULLED

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ENGINE FIRE EXTINGUISHING - BOTTLE DISCHARGE General Each bottle has two discharge assemblies. The discharge assemblies connect the bottles to the discharge manifolds. One manifold goes to discharge nozzles in the left engine nacelle. The other manifold goes to discharge nozzles in the right engine nacelle. Functional Description Explosive squibs in the discharge assemblies connect to the engine fire handles in the flight deck. Squibs for the left engine connect to the left handle. Squibs for the right engine connect to the right handle. A squib for bottle 1 fires when you rotate the related fire handle to DISCH 1. A squib for bottle 2 fires when you rotate the related handle to DISCH 2. When a squib fires, the bottle releases the halon into the engine nacelle. A pressure switch monitors the pressure in each bottle. The switch turns on the discharge indicator light when the bottle pressure decreases. The switch also causes advisory and status messages to show. Training information Point Rigid tubes, color coded yellow, connect both bottles to the left engine nacelle. Flexible braided hoses, with a strip of blue tape, connect both bottles to the right engine nacelle. This color code prevents incorrect connection.

NOZZLES ON STRUT

1

2

NOZZLE ON ENGINE (1 EACH SIDE) FWD CARGO COMPARTMENT

RIGHT ENGINE (LEFT SIMILAR)

DISTRIBUTION TUBE

L ENG OVHT

ENG BTL 1 DISCH

ENG BTL 2 DISCH

DISCH 1

L E F T

2

1

2

R ENGINE FIRE CONTROL PANEL (P8) L ENGINE

CARGO SIDEWALL

FWD CARGO BAY FLOOR ENGINE FIRE BOTTLES

ENGINE FIRE EXTINGUISHING - BOTTLE DISCHARGE B767-3S2F Page - 39

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1

R ENG OVHT

DISCH 2

R I G H T

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ENGINE FIRE EXTINGUISHING - ENGINE FIRE CIRCUIT SWITCH - OPERATION General The engine fire switch includes these components: • Solenoid • Fire warning lights • Two sets of electrical contacts One set of contacts controls engine functions. The other set of contacts controls the engine fire extinguishing system. Solenoid and Warning Light Operation The solenoid energizes if an engine has a fire. This releases the fire handle so you can pull it. The engine fire warning lights come on to show the correct handle to use. The same condition normally occurs in both engine fire switches when you do a fire/overheat test. You can override the solenoid with the engine fire override button. Out Position The operations that happen when you pull the fire handle are on the chart.

SW UNLOCK SOLENOID FIRE HANDLE LIGHTS R FIRE HANDLE LIGHTS

R

R

R

NORMAL

FIRE SWITCH (TYPICAL)

SYSTEM

FUNCTION WHEN PULLED

GENERATOR

TRIPS ENG GENERATOR FIELD RELAY AND GCB

FIRE DETECTION

UNLOCKS FIRE SWITCH SOLENOID AND TURNS ON FIRE SWITCH WHEN ENG FIRE IS DETECTED

ENGINE FIRE EXTINGUISHING

DISCHARGES FIRE EXTINGUISH AGENT WHEN FIRE SWITCH IS PULLED AND THEN TURNED

ENGINE FUEL SHUTOFF VALVE

CLOSES REAR SPAR FUEL SHUTOFF VALVE

CAUTION & WARNING

RESETS FIRE BELL AND SHOWS MESSAGE FOR ENG SHUTDOWN ON CAUTION ANNUNCIATOR

HYDRAULIC POWER

PNEUMATICS

CLOSES ENG HYDRAULIC PUMP SUPPLY SHUTOFF VALVE

CLOSES PRESSURE REGULATION AND SHUTOFF VALVE (PRSOV)

FUEL CONDITION SHUTS OFF ENGINE FUEL CONDITIONING ACTUATOR CONTROL

FIRE

ENGINE T/R CONTROL

REMOVES POWER TO T/R ISOLATION VALVE

FIRE SWITCH (INTERNAL CONTACTS)

ENGINE FIRE EXTINGUISHING - ENGINE FIRE CIRCUIT SWITCH - OPERATION B767-3S2F Page - 41

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ENGINE FIRE EXTINGUISHING - CIRCUIT - FUNCTIONAL DESCRIPTION Bottle Discharge The engine fire switch sends power from the hot battery bus to the engine fire extinguishing bottle squibs. To discharge the bottle, pull out the handle and turn the handle clockwise or counterclockwise. The DISCH 1 position operates the squib for bottle 1. The DISCH 2 position operates the squib for bottle 2. Discharge Indication When pressure in the bottle decreases, the pressure switch closes and makes a ground for the discharge indicator light. The ground also causes EICAS to show advisory and status messages. Training Information Point You can do a check of the pressure switch circuit on the ground. Push and hold the test button to close the switch. The bottle discharge light in the flight deck should come on. Bottle discharge advisory and status messages should show.

ENG BTL 1 MD&T

A A

P

TEST BUTTON

ENG BTL 1 DISCH ENG BTL 2 MD&T

A A

EICAS COMPUTER ADVISORY MSG

PRESSURE SWITCH

ENG BTL 2 DISCH

28V DC HOT BAT BUS

DISCH 1 L ENG SQUIB

FIRE EXT L ENG BTL 1

ENGINE FIRE EXTINGUISHING BOTTLE 1 P

28V DC HOT BAT BUS FIRE EXT L ENG BTL 2

PRESSURE SWITCH

DISCH 2 LEFT ENGINE FIRE SW

P6-1 MN PWR DIST

L ENG SQUIB ENGINE FIRE EXTINGUISHING BOTTLE 2

ENGINE FIRE EXTINGUISHING - CIRCUIT - FUNCTIONAL DESCRIPTION B767-3S2F Page - 43

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TEST BUTTON

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APU FIRE DETECTION - INTRODUCTION & LOCATION Purpose The APU fire detection system warns the flight or ground crew if there is an APU fire. The APU stops automatically if there is a fire. The APU has a fire extinguishing bottle forward of the APU firewall. You can stop the APU and discharge the extinguishing bottle from the P8 panel in the flight deck and the P40 panel on the nose gear.

Nose Landing Gear Component Location The P40 service and APU shutdown panel is on the nose landing gear. The panel has an APU fire warning horn and an APU fire warning light.

P40 PANEL

FIRE DETECTOR APU FIRE WARNING HORN

APU FIRE WARNING HORN

FWD

APU BTL DISCH

APU FIRE WARNING LIGHT

FIRE BOTTLE ARMED

APU FIRE

BOTTLE DISCHARGED

APU SHUTDOWN

APU BOTTLE DISCHARGE

APU

DISCH

FLIGHT DECK CALL

FLIGHT INPH

SERVICE INPH

EMER EXIT WHEELWELL LT TEST RS LIGHTS

OFF LS

APU FIRE CONTROL PANEL (P8)

P40 SERVICE AND APU SHUTDOWN PANEL

APU FIRE DETECTION - INTRODUCTION & LOCATION B767-3S2F Page - 45

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GENERAL DESCRIPTION General The APU fire detection system has these components: • APU fire detectors • Fire detection card • AFOLTS card When a detector card for an APU fire detection loop senses a fire, it sends a signal to the automatic fire/overheat logic test system (AFOLTS) card. The AFOLTS card uses AND logic, for example, both detector loops 1 and 2 must sense a fire for alarm signals to be sent. When there is an APU fire, the AFOLTS card gives these indications: • • • • • •

Warning light Fire bell APU fire handle light in red and unlocks EICAS warning message, APU FIRE APU remote shutdown panel warning light APU warning horn when airplane is on ground

Also, when there is an APU fire, the APU shuts down. To do a test of the system, push the ENG APU/CARGO test switch on the P8 test panel. This test gives flight compartment indications for engine fire and overheat. APU shutdown is prevented during the test. The APU fire detection system has continuous and power-up tests. These tests do not send flight compartment verification, but failed APU loops show on the status and maintenance pages of EICAS. When any test finds both loops defective, the system FAIL light comes on and the EICAS advisory message FIRE/OVHT SYS shows.

AURAL WARNING

WARNING CAUTION

FIRE

CONFIG

PULL UP

A/P DISC

CABIN ALT

OVSPD

APU FIRE (A) FIRE/OVHT SYS (C)

P7 (2)

BELL/ CHIME AURAL & MASTER WARNING MODULES

DISCRETE WARNING DISPLAY (P1-3) ALARM WARNING SIGNAL 1

L (R) EICAS COMPUTERS (E8)

WARNING ELEC UNIT (P51)

AFOLTS CARD 3

LOOP 1 AND LOOP 2 ALARM/FAULT SIGNALS DUAL LOOP FAULT SIGNAL ALARM WARNING SIGNAL 2

STATUS/MAINT

APU FIRE LP 1 APU FIRE LP 2

APU SHUTDOWN 1

EICAS DISPLAY UNITS (P2) APU FIRE WARNING HORN

GND

DET 1

APU TEST APU FIRE

DET 2

BOTTLE DISCHARGED

FIRE DETECTION CARD FILE (P54) LOOP 1 DETECTOR

APU BTL DISCH


ENG/APU CARGO

DISCH

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FLIGHT DECK CALL

SERVICE INPH

EMER EXIT LT TEST RS

WHEELWELL LIGHTS

LS


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INHIBITED DURING TEST

B767-3S2F

APU

FLIGHT INPH

AFT CONTROL STAND (P8)

LOOP 2 DETECTOR

APU SHUTDOWN

SYS FAIL

FAIL P-RESET

1

FIRE BOTTLE ARMED


P40 APU REMOTE SHUTDOWN PANEL

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NOSE LANDING GEAR COMPONENT LOCATION Nose Landing Gear Component Location The P40 service and APU shutdown panel is on the nose landing gear. The panel has an APU fire warning horn and an APU fire warning light.




FIRE BOTTLE ARMED

APU FIRE

BOTTLE DISCHARGED

APU SHUTDOWN BUTTON

APU SHUTDOWN


NOSE LANDING GEAR APU BTL DISCH FLIGHT DECK CALL

DISCH

APU

FLIGHT INPH

SERVICE INPH


OFF LS



NOSE LANDING GEAR COMPONENT LOCATION B767-3S2F Page - 49

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BOTTLE ARMED LIGHT BOTTLE DISCHARGE LIGHT

BOTTLE DISCHARGE BUTTON

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APU FIRE DETECTORS Purpose The APU fire detectors detect fire or high temperatures in the APU compartment. The alarm signal shuts down the APU. Physical Description There are two fire detector assemblies. Each detector assembly has a loop 1 detector and a loop 2 detector attached to a support tube. The upper and lower fire detectors connect to make loop 1 and loop 2. The fire detector assemblies have two sensing elements attached to a stainless steel support tube. The sensing element is used to find a fire or a temperature that is too hot. It consists of an Inconel tube with two electrical conductors in a thermistor material. The thermistor material in the Inconel tube decreases resistance when the material is heated. Location The upper detector assembly is attached to the airframe and the APU inlet plenum. The lower detector assembly is attached to the left APU access door.

UPPER FIRE DETECTOR ASSEMBLY

APU COMPARTMENT (SIDE VIEW)

LOWER FIRE DETECTOR ASSEMBLY (LEFT APU ACCESS DOOR)

ELEMENT

APU FIRE DETECTOR ASSEMBLY (TYPICAL)

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SUPPORT TUBE

ATTACHMENT LUG

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FIRE DETECTORS - FUNCTIONAL DESCRIPTION Functional Description The fire detector assemblies have two sensing elements attached to a stainless steel support tube. The sensing element is used to find a fire or a temperature that is too hot. It consists of an Inconel tube with two electrical conductors in a thermistor material. The thermistor material in the Inconel tube decreases resistance when the material is heated. At normal ambient temperatures the sensing element resistance is high. The resistance decreases quickly as the element temperature increases. When the resistance decreases to a set point, an alarm signal goes to the AFOLTS card. If an electrical short occurs, the resistance decreases faster than when the high temperature causes the resistance change. The electrical short causes the logic in the detector card to send a fault signal to the AFOLTS card. When the temperature decreases, the resistance increases above the reset value and the alarm signal stops.

SUPPORT TUBE QUICK RELEASE CLAMP ELECTRICAL CONNECTION LOOP 1

ELECTRICAL CONNECTION LOOP 2

HEAT SENSITIVE ELECTRICALLY CONDUCTIVE MATERIAL (AS TEMPERATURE RISES, CONDUCTIVITY INCREASES)

1/16 INCH

OUTER STEEL TUBE (GROUNDED) APU FIRE DETECTOR

CENTRAL CONDUCTORS (INPUT TO DETECTOR CARD)

FIRE DETECTORS - FUNCTIONAL DESCRIPTION B767-3S2F Page - 53

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AFOLTS CARD - FUNCTIONAL DESCRIPTION - SINGLE LOOP & DUAL LOOP

mode with different logic. If the two loops have failures, a SYS FAIL light shows on the P8 panel, and a FIRE/OVHT SYS advisory message shows on the flight compartment display.

General - Dual Loop

Detector, card, or related wiring failures do not always give a valid fault output at the time of a failure. You must use the system test to find these loop failures.

The automatic fire and overheat logic and test system (AFOLTS) cards shows fire conditions when the detector cards receive alarm or fault signals from the fire detection loops 1 and 2. Outputs from the AFOLTS card give indications and flight compartment messages. The cards can operate in the dual loop mode (normal) or in a single loop mode. An AFOLTS card receives alarm and fault signals from two detector cards. The detector cards connect to fire detection loops 1 and 2. During dual loop mode operation an alarm or fault signal is necessary from the two detector cards to make an alarm warning of a fire condition. General - Single Loop The automatic fire/overheat logic test system (AFOLTS) can operate in a dual loop mode or a single loop mode. The AFOLTS card selects a faulty detection loop off, after that loop fails a test. The test can be a self-test started when power connects to the battery bus or for a power interruption of more than two milliseconds, or the test can be a manual test from the P8 panel. After an AFOLTS card finds a faulty loop in the fire detection system, only a single alarm or fault signal is necessary from the remaining good loop. If a fire condition is found in the single loop mode, flight compartment warning and indications are the same as for the dual loop mode. Test When the card is in the dual loop mode, the card monitors loop 1 and loop 2 detector cards. If the detector card finds a fault with one or two of its loops during a power-up self-test or a manual test from the P8 panel, a fault signal goes to the AFOLTS card. AFOLTS sends status and maintenance messages to the flight compartment to show which loop has a failure. After a fault is found on one loop, the system does not use that loop and operates in the single loop

Flight Compartment Messages If the two loops have an output (alarm), the flight compartment warning message shows, and the loop status messages do not show. Automatic 60-Minute Test The AFOLTS card gives a self-test command to the detection zones when the detection loops, fire/overheat/smoke, in a zone are in disagreement for more than five seconds, or the zone is already in the single loop mode. The AFOLTS card gives the self-test command again each 60 minutes if the initial condition does not change or stays in the single loop operation.

LOOP MSG (S/M)

SYS FAIL LIGHT EICAS LOOP 1

FIRE/OVHT SYS


LOOP MSG (S/M) (ADVISORY)


TEST SEQUENCER

L EICAS COMPUTER

FAULT TEST

LOOP MSG (S/M)

ALARM TEST

EICAS LOOP 2

FIRE/OVHT SYS

FAULT TEST LOOP 1 DETECTOR CARD

T

LOOP 2 T DETECTOR CARD

2

R EICAS COMPUTER

SOFTWARE FAULT ALARM

P54

LOOP MSG (S/M) (ADVISORY)

2

FAULT ALARM

P54

ALARM + ALARM = ALARM ALARM + FAULT = ALARM FAULT + ALARM = ALARM FAULT + FAULT = FAIL LIGHT

ALARM 1

1 FIRE DISCRETE ANNUN (P1-3)

ALARM 2 1FIRE SW LIGHTS (P8) 2 FIRE SW LOCK RELEASE (P8) 3 FUEL CONT SW LIGHT (P8)

ALARM OR FAULT + NOTHING FOR MORE THAN 5 SEC = TEST EACH 60 MINUTES AFOLTS (TYP) (P54)

NOTE: STATUS LOOP MSGS INHIBITED DURING AN ALARM MAINTENANCE LOOP MSGS SHOW DURING AN ALARM 1

STARTS BY NOSE STRUT EXTENSION ON TAKEOFF

2

CIRCUIT NOT IN OPERATION SIGNAL FOUND BY A FAILED TEST

MASTER WARN NOT PUSHED RADIO ALTM <400 FEET

1 MASTER WARNING LIGHTS (P7) 2 FIRE WARNING BELL

<20 SEC AFTER TAKEOFF 1 WARNING ELECTRONICS UNIT (P51)

AFOLTS CARD - FUNCTIONAL DESCRIPTION - SINGLE LOOP & DUAL LOOP B767-3S2F Page - 55

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APU FIRE DETECTION - INDICATIONS Purpose The nose gear panel lets the ground crew stop operation of and extinguish the fire in the APU from the ground. The flight compartment also has a panel to stop operation of the APU and release the contents of the fire extinguishing bottle. Physical Description The flight compartment panel has a fire warning light and a T-handle to release the contents of the extinguishing bottle. The panel has a bottle discharge light. The P40 panel has an APU fire warning horn and an APU FIRE warning light. The panel has an APU SHUTDOWN button. The panel also has a FIRE BOTTLE ARMED light, APU BOTTLE DISCHARGE button, and BOTTLE DISCHARGED light.




FIRE BOTTLE ARMED

APU FIRE

BOTTLE DISCHARGED

APU SHUTDOWN BUTTON

APU SHUTDOWN


NOSE LANDING GEAR APU BTL DISCH FLIGHT DECK CALL

DISCH

APU

FLIGHT INPH

SERVICE INPH


OFF LS



APU FIRE DETECTION - INDICATIONS B767-3S2F Page - 57

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BOTTLE ARMED LIGHT BOTTLE DISCHARGE LIGHT

BOTTLE DISCHARGE BUTTON

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APU FIRE EXTINGUISHING - INTRODUCTION

An explosive squib in the discharge assembly releases the halon from the bottle. The squib connects to the fire switches.

Purpose

A pressure switch monitors the pressure in the bottle. After the bottle releases its content, the switch causes the discharge indicator lights to come on. The switch also causes EICAS advisory and status messages to show.

The APU fire extinguishing system extinguishes fires in the APU compartment. General If there is a fire, you can release the APU fire extinguisher bottle content manually from the P8 APU fire control panel or from the P40 APU remote control panel. The APU fire extinguishing system has these components: • • • • •

APU fire extinguishing bottle APU fire extinguishing bottle squib Cargo fire/engine control module APU fire switches APU remote control panel (P40)

A bottle is forward of the APU fire wall on the lower right side. When you release the bottle content, a nozzle moves the extinguishing agent to the APU compartment. The bottle releases its content by a squib. Control of the squib comes from the flight compartment or from the APU remote control panel on the nose landing gear. Flight compartment operation is with the APU fire handle on the P8 panel. This handle locks down by a solenoid that releases for an APU fire. After you pull the fire handle, you can turn it in either direction to release the bottle contents. A bottle discharge light on the P8 panel and also on the P40 panel comes on when the bottle pressure decreases. EICAS messages and indicator lights show when the bottle pressure is low. Operation The APU fire extinguishing bottle holds halon fire extinguishing agent pressurized with nitrogen. A discharge assembly connects the bottle to a discharge tube. The tube goes to a discharge nozzle in the APU compartment.

APU

FIRE EXTINGUISHING BOTTLE APU FIRE WARNING HORN

SERVICE ACCESS

APU FIRE

FIRE BOTTLE ARMED

BOTTLE DISCHARGED

APU FIRE SHUTDOWN

FLIGHT DECK CALL

SERVICE INPH

L

ENG

R

2

APU

1

CARGO 2 2A


OFF LS


APU REMOTE CONTROL PANEL (P40) (NOSE LANDING GEAR)

B767-3S2F Page - 59

TEST 1

APU


DISCH

FLIGHT INPH

SQUIB TEST

APU BTL DISCH

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TEST 1 FWD TEST 2 AFT

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APU FIRE EXTINGUISHING - GENERAL DESCRIPTION General The APU fire extinguishing system has these components: • • • • •

APU fire extinguishing bottle APU fire extinguishing bottle squib Cargo fire/engine control module APU fire switches APU remote control panel (P40).

A bottle is forward of the APU fire wall on the lower right side. When you release the bottle content, a nozzle moves the extinguishing agent to the APU compartment. The bottle releases its content by a squib. Control of the squib comes from the flight compartment or from the APU remote control panel on the nose landing gear. Flight compartment operation is with the APU fire handle on the P8 panel. This handle locks down by a solenoid that releases for an APU fire. After you pull the fire handle, you can turn it in either direction to release the bottle contents. A bottle discharge light on the P8 panel and also on the P40 panel comes on when the bottle pressure decreases. EICAS messages and indicator lights show when the bottle pressure is low. Operation The APU fire extinguishing bottle holds halon fire extinguishing agent pressurized with nitrogen. A discharge assembly connects the bottle to a discharge tube. The tube goes to a discharge nozzle in the APU compartment. An explosive squib in the discharge assembly releases the halon from the bottle. The squib connects to the fire switches. A pressure switch monitors the pressure in the bottle. After the bottle releases its content, the switch causes the discharge indicator lights to come on. The switch also causes EICAS advisory and status messages to show.

APU

FIRE EXTINGUISHING BOTTLE SERVICE ACCESS


FIRE BOTTLE ARMED

APU FIRE

APU BTL DISCH

BOTTLE DISCHARGED

APU FIRE SHUTDOWN


DISCH

FLIGHT DECK CALL

FLIGHT INPH

SERVICE INPH

EMER EXIT LT TEST

APU

WHEELWELL LIGHTS

OFF

APU REMOTE CONTROL PANEL (P40)


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APU FIRE EXTINGUISHING - EXTINGUISHING BOTTLE


Purpose

To do a test of the switch circuits, push the manual override button on the pressure switch housing.

The APU fire extinguishing bottle contains the Halon fire extinguishing agent. Location The fire extinguishing bottle is on the forward side of the APU fire wall, in the control bay. Physical Description The fire extinguishing bottle has these components: • • • •

Safety relief and fill port Pressure switch Squib Two discharge assemblies

The fire extinguishing bottle is interchangeable with the engine fire extinguishing bottles. Caps cover one squib and discharge port. Functional Description The bottle contains halon fire extinguishing agent pressurized with nitrogen. If the pressure in the bottle becomes too high, the safety relief port opens. The discharge assembly has an explosive squib. An electric current from the fire extinguishing circuit fires the squib. This ruptures the frangible disk which releases the halon through the discharge port. The pressure switch gives control panel indications when bottle pressure decreases. The switch monitors the pressure inside the bottle and is normally open. When the bottle pressure decreases because of a leak or bottle discharge, the switch closes and causes an EICAS message, APU BTL 1/2.

The squib can be removed and replaced without damage to the rupture disc. There is no squib installed on the unused discharge port. The unused port is capped off.

WARNING: INSTALL THE PROTECTIVE COVER ON THE SQUIB WHEN THE AIRPLANE WIRING IS DISCONNECTED FROM THE SQUIB. INCORRECT PROCEDURES OR EQUIPMENT COULD FIRE THE SQUIB AND CAUSE INJURY.

MANUAL OVERRIDE BUTTON

ELECTRICAL CONNECTOR

PRESSURE SWITCH

FRONT VIEW

FRANGIBLE DISK

FWD

SCREEN SQUIB CAP LOOKING OUTBOARD TO THE RIGHT SIDE

DISCHARGE ASSEMBLY

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APU FIRE CONTROL PANEL Purpose The cargo/APU fire control panel permits flight deck control of the APU and cargo fire extinguishing systems. Location The cargo/APU fire control panel is in the flight deck on the P8 aisle stand panel. Physical Description The cargo/APU fire control panel has a fire switch for the APU and a discharge light for the APU fire bottle. Quick release fasteners attach the module to the aisle stand structure. Electrical connectors connect the airplane wires to the panel.

ARMED

ARMED

FWD

AFT

FWD

ARM

APU BTL DISCH

AFT

CARGO FIRE BTL DISCH

DISCH

DISCH


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APU

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APU FIRE EXTINGUISHING - APU FIRE CONTROL PANEL & SWITCHES

The fire warning light uses four lamps. Functional Description

Purpose The cargo/APU fire control panel permits flight deck control of the APU and cargo fire extinguishing systems. Location The cargo/APU fire control panel is in the flight deck on the P8 aisle stand panel.

The solenoid locks the fire switch so you cannot pull it accidently. If the APU has a fire, the fire warning light comes on and the solenoid energizes to release the switch. When you pull the fire switch, the push-pull switch contacts isolate the APU from the airplane systems. When the switch is out, you can turn it left or right to a mechanical stop at the discharge position. The rotary switch contacts close and operate the fire extinguishing system.

Physical Description The cargo/APU fire control panel has a fire switch for the APU and a discharge light for the APU fire bottle. Quick release fasteners attach the module to the aisle stand structure. Electrical connectors connect the airplane wires to the panel. Purpose The APU fire switch gives an indication of an APU fire and controls the APU fire extinguishing system. Location The APU fire switch is on the APU/cargo fire control panel. Physical Description The APU fire switch includes these parts: • • • • •

APU fire warning light Solenoid APU fire override button Push-pull switch contacts (internal not shown) Rotary switch contacts (internal not shown)

When you release the switch, a spring moves the switch a small distance from the discharge position to open the rotary switch contacts. The fire override button lets you pull the fire switch when the solenoid is not energized. You must put the switch back to the center position before you can push the switch in. Training Information Point The engine and APU fire switches are not interchangeable. The fire warning light labels and the electrical connectors are different. When operating the fire switches in the discharge position, make sure that the fire bottle discharge light illuminates.

DISCHARGE (SWITCH CLOSED) SPRING RETURN (SWITCH OPEN)

APU BTL DISCH

CENTER DISCH

DISCH


APU

APU

SPRING RETURN (SWITCH OPEN) DISCHARGE (SWITCH CLOSED) APU/CARGO FIRE CONTROL PANEL (P8)

SWITCH POSITIONS

APU FIRE OVERRIDE BUTTON PUSHED

SOLENOID ENERGIZED

SWITCH LOCKED

SWITCH RELEASED MANUALLY

SWITCH RELEASED ELECTRICALLY

APU FIRE EXTINGUISHING - APU FIRE CONTROL PANEL & SWITCHES B767-3S2F Page - 67

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SWITCH PULLED

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APU FIRE SWITCH - OPERATION Warning Light and Solenoid Operation The APU fire warning light comes on if there is an APU fire. The solenoid energizes and releases the fire switch so you can pull it. This also occurs when you do a fire/overheat test. Out Position When you pull the fire switch, these functions occur: • • • • • •

Generator field trips APU fuel shutoff valve closes APU shutoff valve closes APU stops EICAS messages which are not necessary do not show Fire warnings at the P40 panel are canceled

Discharge Positions The left or right DISCH position operates the APU fire extinguishing bottle squib.

SW UNLOCK SOLENOID FIRE HANDLE LIGHTS R FIRE HANDLE LIGHTS

R

R

R

NORMAL

FIRE SWITCH (TYPICAL)

SYSTEM GENERATOR FIRE DETECTION APU

FIRE

FUNCTION WHEN PULLED TRIPS APU GENERATOR FIELD RELAY AND GCB SHUTS OFF APU FIRE HORN AIRPLANE ON GROUND AND REMOTE FIRE LIGHT AT NOSE GEAR UNLOCKS FIRE SWITCH SOLENOID. TURNS ON FIRE SWITCH WHEN APU FIRE DETECTED

ENGINE FIRE EXTINGUISHING

DISCHARGES FIRE EXTINGUISHING AGENT WHEN FIRE SWITCH IS PULLED AND THEN TURNED LEFT OR RIGHT

ENGINE FUEL SHUTOFF VALVE

CLOSES APU FUEL VALVE

CAUTION AND WARNING

RESETS FIRE BELL

PNEUMATICS

CLOSES AIR SUPPLY APU VALVE

APU IGNITION AND SHUTS DOWN APU WHEN FIRE HANDLE IS PULLED STARTING

FIRE SWITCH (INTERNAL CONTACTS)

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FUNCTIONAL DESCRIPTION - CIRCUIT General Power for the APU fire handle on the P8 panel and the APU shutdown switch on the APU remote panel (P40) comes from the 28v dc hot battery. When you pull the fire handle or push the external shutdown switch, the APU fire extinguisher arms. The fire handle normally has a lock until there is a fire. After you pull the fire handle or push the external shutdown switch, you turn the fire handle or push the APU bottle discharge switch on the P40 APU remote control panel to release the fire extinguisher content. The APU access doors must be closed for the fire extinguisher to have the correct effect. When the pressure in the bottle decreases, the pressure switch on the bottle closes and connects a ground to the APU bottle discharge lights. Training Information Point To do a test of the bottle discharge light circuit, you push the test button on the pressure switch assembly. This button connects the circuit and causes the two bottle discharge lights (P40 and P8) to come on. The message APU BTL also shows on the EICAS display.

28V DC HOT BAT BUS FIRE EXT APU 1 P6 CB PANEL

(CCW) 1 (CW)

APU BTL DISCH

SQUIB <400 PSI

MD&T

P PRESS SWITCH

APU FIRE SWITCH APU/CARGO FIRE CONTROL PANEL (P8)

28V DC BAT BUS

A

APU REMOTE FIRE IND P11 CB PANEL

FIRE BOTTLE ARMED A

BOTTLE DISCHARGED APU G

APU BOTTLE DISCHARGE APU REMOTE CONTROL (APU SHUTDOWN) PANEL (P40) 2 K421 EXTERNAL SHUTDOWN (P37)

TEST 1 SQUIB TEST PANEL (P61) 1

PULL TO STOP APU, TURN TO RELEASE BOTTLE CONTENT

2

APU FIRE SW PUSHED P40

FUNCTIONAL DESCRIPTION - CIRCUIT B767-3S2F Page - 71

APU FIRE EXT BOTTLE

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APU BTL EICAS COMPUTER ADVISORY MSG

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FREIGHTER LAVATORY - SMOKE DETECTION SYSTEM GENERAL DESCRIPTION General The smoke detection system uses the JAMCO smoke detector. This smoke detector uses the ionization type system. The alarm is self contained in the unit along with a test button and a horn silencing button. System Tests The smoke detector is tested on the unit.

ALARM HORN

SMOKE DETECTOR

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LOWER CARGO COMPARTMENT SMOKE DETECTION INTRODUCTION Purpose The system gives a FWD or AFT CARGO FIRE WARNING indication in the flight compartment when smoke is detected in the air of the forward or aft cargo compartments.

AFT CARGO COMPARTMENT

SMOKE DETECTORS (2)

FWD CARGO COMPARTMENT

SMOKE DETECTORS (2)

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LOWER CARGO COMPARTMENT SMOKE DETECTION - GENERAL DESCRIPTION Purpose There are different smoke detection systems for each cargo compartment. The smoke detectors are connected to a venturi ejector system to move air through the sampling tubes past the light diodes. General The detectors operate when the pneumatic system is powered to move air through the sampling tubes. During AND logic (normal) operation, the two detectors must sense smoke to cause fire signals 1 and 2 to go to the AFOLTS card. During OR logic (one detector failure) operation, only one detector is necessary to send a signal to the AFOLTS card. System Tests AFOLTS card 6 monitors and does a test of the smoke detectors (fwd/aft). The annunciator lights and EICAS messages show this data: • • • •

Location of a fire Smoke detector with a failure Detector fan with a failure System (fwd/aft) with a failure.

You can use the ENG/APU/CARGO FIRE test switch to start a manual test. This test is almost the same as the power-up test. General Component Locations The smoke detector assemblies for the forward cargo compartment are located with the main deck smoke detector assemblies for zones A, B, and C. The smoke detectors are located on the left side of the lower forward cargo compartment across from the forward cargo door. The smoke detector assemblies for the aft cargo compartment are located with the main deck smoke detectors for zones D, E, and F. The smoke detectors are located on the left side of the aft lower cargo compartment across from the aft cargo door.

AFOLTS card No. 6 is in the fire detection card file (P54). The cargo fire detectors are tested from the FIRE/OVHT test panel (P8) using the same test switch for engine and APU fire loops.

WARNING AFT CARGO COMPARTMENT

FWD CARGO COMPARTMENT

FIRE

CONFIG

PULL UP

A/P DISC

CABIN ALT

OVSPD

CAUTION P7 (2)

FIRE BELL (2) BELL/CHIME AURAL & MASTER WARNING MODULES

FWD CARGO FIRE FIRE/OVHT SYS

STATUS/MAINT

FWD CARGO DET 1 FWD CARGO DET 2

SMOKE DET ASSEMBLY ALARM WARNING SIGNAL NO 1



LOOP 1 AND LOOP 2 ALARM/FAULT SIGNALS

CARGO FIRE ARMED


FWD

ALARM WARNING SIGNAL NO 2 ARMED

SYSTEM MANUAL TEST AFOLTS CARD 6

FWD A R M AFT DEPR/ DISCH

AFT

FWD CARGO DET 1 FWD CARGO DET 2




ENG/APU CARGO

2

A R M

SYS FAIL

DEPR DISCH

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A

1

ARMED FAIL P-RESET

FIRE/OVHT TEST PANEL (P8)

MAIN

MAIN

CARGO FIRE CONTROL PANEL (P8)

LOWER CARGO COMPARTMENT SMOKE DETECTION - GENERAL DESCRIPTION B767-3S2F

DISCH


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FLIGHT DECK CONTROLS Component Locations These are the components in the flight deck that have an interface with the lower cargo compartment smoke detection system: • • • •

Master warning and caution (P7) FIRE/OVHT test panel (P8) Fire bell (2) Discrete warning display (P1-3)

WARNING CAUTION P7 (2)

FIRE BELL (2)

CARGO FIRE ARMED FWD

FIRE/OVHT TEST ENG/APU CARGO

WHL WELL

ARMED

SYS FAIL

DEPR DISCH

DISCH 1

ARMED MAIN

MAIN


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A R M

FIRE TEST PANEL (P8)

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A R M AFT DEPR/ DISCH

AFT

FAIL P-RESET

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A

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LOWER CARGO COMPARTMENT COMPONENT LOCATION General Component Locations The smoke detector assemblies for the forward cargo compartment are located with the main deck smoke detector assemblies for zones A, B, and C. The smoke detectors are located on the left side of the lower forward cargo compartment across from the forward cargo door. The smoke detector assemblies for the aft cargo compartment are located with the main deck smoke detectors for zones D, E, and F. The smoke detectors are located on the left side of the aft lower cargo compartment across from the aft cargo door. AFOLTS card No. 6 is in the fire detection card file (P54). The cargo fire detectors are tested from the FIRE/OVHT test panel (P8) using the same test switch for engine and APU fire loops.

SMOKE SAMPLING PORTS

FROM SAMPLING PORTS

AFT CARGO SMOKE DETECTOR 1 AFT CARGO SMOKE DETECTOR 2

MAIN DECK SMOKE DETECTOR FROM SAMPLING PORTS

TO VENTURI EJECTOR

TO VENTURI EJECTOR

AFT DETECTORS

MAIN DECK SMOKE DETECTOR FWD CARGO SMOKE DETECTOR 1 FWD CARGO SMOKE DETECTOR 2 FORWARD DETECTORS

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LOWER CARGO COMPARTMENT SMOKE DETECTION SMOKE DETECTOR Purpose The smoke detectors monitor air in the cargo compartments for smoke. The venturi ejector provides the source of power to move the air from the cargo compartment into the smoke detector. Physical Description All cargo compartment smoke detectors are identical and interchangeable. The detector consists of a photo diode and light emitting diode (LED) in a chamber. There are two printed wiring board assemblies in each chamber. The detector has inlet and outlet tubes that protrude from the chamber to give airflow through the detector. Functional Description The smoke detector uses an optical principle to detect smoke. The detector consists of a photodiode and light emitting diode (LED) in a chamber. The detector has inlet and outlet tubes for air access. The beam of light from the light emitting diode shines into a light trap. The smoke particles reflect part of the beam of light onto the photodiode. The photodiode current increases with the amount of smoke that enters the detector. When the voltage is more than a preset level, a relay energizes to provide an alarm signal

AIR IN SMOKE SAMPLING PORTS

ELECTRICAL CONNECTOR SMOKE PARTICLES LED INTENSITY CONTROL PHOTO DIODE

ALARM PHOTO DIODE

LIGHT BEAM NON-REFLECTIVE SURFACE

FROM SAMPLING PORTS

TO VENTURI EJECTOR MAIN DECK SMOKE DETECTOR

FWD CARGO SMOKE DETECTOR 1 FWD CARGO SMOKE DETECTOR 2

AIR OUT SMOKE DETECTOR INTERNAL

FORWARD DETECTORS

LOWER CARGO COMPARTMENT SMOKE DETECTION - SMOKE DETECTOR B767-3S2F Page - 83

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LOWER CARGO COMPARTMENT SMOKE DETECTION DETECTOR LOCATION Component Location The forward cargo smoke detector assemblies are on the left side of the forward cargo compartment next to the main deck detectors zones A, B, and C. The smoke detectors are opposite the cargo door in the forward compartment. The aft cargo smoke detectors are on the left side of the aft cargo compartment next to the main deck detectors zones D, E, and F. The smoke detectors are opposite the cargo door in the aft compartment. AFOLTS card 6 is in the P54 fire detection card file. The cargo fire detector tests are done from the FIRE/OVHT test panel (P8) with the same test switch for engine and APU fire loops.

SMOKE DETECTORS

SMOKE SAMPLING PORTS

FROM SAMPLING PORTS

TO VENTURI EJECTOR MAIN DECK SMOKE DETECTOR

FWD CARGO SMOKE DETECTOR 1 FWD CARGO SMOKE DETECTOR 2 FORWARD DETECTORS

JOINS VENTURI EJECTOR

SMOKE DETECTOR ASSEMBLY

LOWER CARGO COMPARTMENT SMOKE DETECTION - DETECTOR LOCATION B767-3S2F Page - 85

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LOWER CARGO COMPARTMENT SMOKE DETECTION SMOKE DETECTOR - FUNCTIONAL DESCRIPTION Functional Description During normal operation, a beam of light from the light emitting diode shines into the light trap. Photo diode current comes from the light that reflects from the chamber surface. As smoke enters the detector, a portion of the beam of light reflects from the smoke particles onto the photo diode. This causes the photo diode current to increase with the amount of smoke that enters the detector. Amplifiers raise this photo diode current to a detectable voltage level. When the voltage is more than a preset level, a relay energizes to give an alarm signal. A test of the smoke detector verifies that the LED light source is not burned out. The test also makes sure the smoke detector has a minimum guaranteed sensitivity.

AIR IN

ELECTRICAL CONNECTOR AIR IN

ELECTRICAL CONNECTOR SMOKE PARTICLES LED INTENSITY CONTROL PHOTO DIODE

ALARM PHOTO DIODE

LIGHT BEAM NON-REFLECTIVE SURFACE

AIR OUT SMOKE DETECTOR

SMOKE DETECTOR INTERNAL

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INDICATIONS Component Locations These components in the flight compartment have an interface with the lower cargo compartment smoke detection system: • • • •

Master warning and caution on P7 FIRE/OVHT test panel on P8 Discrete warning display on P1-3 Fire bell (2)

FIRE/OVHT TEST

FIRE

CONFIG

PULL UP

A/P DISC

CABIN ALT

OVSPD

WHL WELL

ENG/APU CARGO

SYS FAIL

FAIL P-RESET

FIRE/OVHT TEST PANEL (P8)

DISCRETE WARNING DISPLAY (P1-3) WARNING CAUTION

P-5 PANEL

FIRE BELL (2)

P7 (2)

CARGO FIRE ARMED FWD

ARMED

FWD A R M AFT

DEPR/ DISCH

AFT A R M

DEPR DISCH

ARMED MAIN

MAIN


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DISCH 1

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AFOLTS CARD - FUNCTIONAL DESCRIPTION - DUAL LOOP General The automatic fire and overheat logic and test system (AFOLTS) card shows fire conditions when the detector cards receive an alarm from the smoke detectors. Outputs from the AFOLTS card give indications and flight compartment messages. The cards can operate in the dual loop mode (normal) or a single loop mode. The dual loop mode shows here. An AFOLTS card receives alarm and fault signals from four smoke detectors, two in each of the cargo compartments. Each smoke detector is a loop. During dual loop mode operation, an alarm or fault signal is necessary from the two detector cards to make an alarm warning of a fire condition. EICAS A single loop output shows as a message on the status and maintenance pages. If the two loops have an output (alarm), the EICAS display changes to a warning, and the loop messages do not show. Test When the AFOLTS card is in the dual loop mode, the card monitors loop 1 and loop 2 smoke detectors. If the AFOLTS card finds a fault with one or two smoke detectors for a cargo compartment during a power-up self-test or a manual test from the P8 panel, AFOLTS sends status and maintenance messages to the flight compartment to show which loop has a failure. If the card finds a fault with one loop, the system does not use that loop and operates in the single loop mode with different logic. If the two loops have failures, a SYS FAIL light and FIRE/OVHT SYS advisory message show in the flight compartment. Smoke detectors or related wiring failures do not always give a valid fault output at the time of a failure. You must use a system test to find these loop failures. Automatic 60-Minute Test The AFOLTS card gives a self-test command to the detection zones when the detection loops, fire/overheat/smoke, in a zone are in disagreement for more than five seconds, or the zone is already in the single loop mode.

The AFOLTS card gives the self-test command again each 60 minutes if the initial condition does not change, or the system stays in the single loop operation.

LOOP MSG (S&M)

SYS FAIL LIGHT

EICAS LOOP 1 FIRE/OVHT SYS


LOOP MSG (S&M)


TEST SEQUENCER

L EICAS COMPUTER

FAULT TEST

LOOP MSG (S&M)

ALARM TEST

EICAS LOOP 2

FIRE/OVHT SYS

FAULT TEST SMOKE DETECTOR LOOP 2

LOOP MSG (S&M)

SMOKE DETECTOR LOOP 1

2 FAULT ALARM

P54

FAULT ALARM

2

SOFTWARE ALARM + ALARM = ALARM ALARM + FAULT = ALARM FAULT + ALARM = ALARM FAULT + FAULT = FAIL LIGHT

R EICAS COMPUTER ALARM 1

1 FIRE DISCRETE ANN (P1-3)

ALARM 2

1 FIRE SW LIGHTS (P8) 2 FIRE SW LOCK RELEASE (P8) 3 FUEL CONT SW LIGHT (P8)

ALARM OR FAULT + NOTHING FOR MORE THAN 5 SEC = TEST EACH 60 MINUTES

P54

AFOLTS (TYP) (P54) NOTE: STATUS LOOP MSGS INHIBIT DURING AN ALARM; MAINTENANCE LOOP MSGS SHOW DURING AN ALARM 1

STARTS BY NOSE STRUT EXTENSION ON TAKEOFF

2

CIRCUIT NO OPERATION SIGNAL AS FOUND BY A FAILED TEST

MASTER WARN NOT PUSHED

RADIO ALTM <400 FEET <20 SEC AFTER TAKEOFF 1


AFOLTS CARD - FUNCTIONAL DESCRIPTION - DUAL LOOP B767-3S2F Page - 91

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1 MASTER WARNING LIGHTS (P7) 2 FIRE WARNING BELL

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MAIN DECK CARGO SMOKE DETECTION SYSTEM - GENERAL DESCRIPTION General The smoke detection system for the main deck cargo compartment is divided into 6 zones (Zones A - F). The smoke detection system monitors the air in the cargo compartment and provides alerts for a smoke condition. The main deck cargo compartment uses 12 smoke detectors arranged in 6 pairs making up two loops. Each main deck cargo compartment smoke detector connects to the test alarm interface module (TAIM). The TAIM transmits the status of loop one and loop two signals from the main deck smoke detectors in order to provide alarm signals to AFOLTS. The TAIM is located in the main equipment center by the E3 rack. There is one AFOLTS card for main deck cargo compartment smoke detection. AFOLTS normally uses AND logic. If at least one smoke detector pair (loops 1 and 2) for the main deck sense smoke, you get the following indications: • • • • •

the red MAIN CARGO FIRE switch lights (on P8) the red FIRE light (on P1-3) the red master warning lights (on P7) the fire bell sounds MAIN CARGO FIRE warning message on EICAS

System Tests The cargo smoke detectors are tested from the FIRE/OVHT test panel (on P8), using the same test switch for engine and APU. During a test, the TAIM sends the status of main deck cargo loops 1 and 2 to the AFOLTS card.

WARNING

AURAL INDICATION SPEAKER (WARNING)

CAUTION

FIRE

CONFIG

PULL UP

A/P DISC

P7 (2)

BELL/CHIME AURAL & MASTER WARNING MODULES



MN CARGO FIRE FIRE/OVHT SYS

STATUS/MAINT

MN CARGO LP 1 MN CARGO LP 2

ALARM WARNING SIGNAL NO. 1 WARNING ELECTRONICS UNIT (P51)


LOOP 1 AND LOOP 2 ALARM/FAULT SIGNALS

AFOLTS CARD 7

CARGO FIRE


ARMED FWD

ALARM WARNING SIGNAL NO. 2 SYSTEM MANUAL TEST

ARMED

A R M AFT DEPR/ DISCH

AFT

FIRE DETECTION CARD FILE (P54) WHL WELL

ENG/APU CARGO

SYS FAIL

ARMED MAIN

MAIN DECK LP 2 SMOKE DETECTORS

2

A R M

FIRE/OVHT TEST

MAIN DECK LP 1 SMOKE DETECTORS

TEST/ALARM INTERFACE MODULE (M2039)

FWD

MAIN

FAIL P-RESET

FIRE TEST PANEL (P8)

MAIN DECK CARGO SMOKE DETECTION SYSTEM - GENERAL DESCRIPTION B767-3S2F Page - 93

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DEPR DISCH

DISCH 1

A

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SMOKE DETECTION SYSTEM - VENTURI EJECTOR AND PRESSURE SWITCH Venturi Ejector The venturi ejector uses bleed air to create a vacuum condition to pull sample air through the smoke detectors in the main deck and forward and aft lower cargo compartments. Sample air in each of the zones is drawn through the detectors via a duct distribution system. Smoke entering the light-proof chamber of the smoke detectors reflects the light from the pilot lamp onto the photocell. The photocell gives a signal to an amplifier where the signal is processed and sent to a relay which provides an alarm output signal to the fire/overheat logic test card. The ejector is located aft of the mix manifold in the forward cargo compartment. Pressure Switch The pressure switch is installed on the ejector plenum in the aft end of the forward cargo compartment. When the gauge pressure falls below approximately seven inches of water, the pressure switch closes and causes an EICAS message. When the pressure is eleven inches of water or greater, the pressure switch will open and the EICAS message will disappear.

MIX MANIFOLD EJECTOR

FWD PRESSURE SWITCH EJECTOR AND PRESSURE SWITCH

SMOKE DETECTION SYSTEM - VENTURI EJECTOR AND PRESSURE SWITCH B767-3S2F Page - 95

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MAIN DECK SMOKE DETECTORS Purpose The main deck cargo compartment uses 12 smoke detectors to check for smoke in order to give flight deck indications when there is a fire. Component Location Smoke detectors are near the cargo doors in the forward and aft cargo compartments. The smoke detectors for the forward main deck (zones A, B, and C) are located opposite the FWD cargo door in the lower cargo compartment. The smoke detectors for the aft main deck (zones D, E, and F) are located opposite the AFT cargo door in the lower cargo compartment. Air sampling tubes in the ceiling of each zone connect to the detector pair for that zone. Functional Description The smoke detector uses an optical principle to detect smoke. The detector consists of a photodiode and light emitting diode (LED) in a chamber. The detector has inlet and outlet tubes for air access. The beam of light from the LED shines into a light trap. The smoke particles reflect part of the beam of light onto the photodiode. The photodiode current increases with the amount of smoke that enters the detector. When the voltage is more than a preset level, a relay energizes to provide an alarm signal.

CARGO COMPARTMENT CEILING SMOKE SAMPLING PORTS ZONE F ZONE E INTAKE ORIFICE

ZONE D ZONE C

FROM SAMPLING PORTS

ZONE B ZONE A

ZONE F FROM SAMPLING PORTS

ZONE C ZONE B

ZONE E TO VENTURI EJECTOR LOOP 1 LOOP 2 LOOP 1 LOOP 2

ZONEA

LOWER LOBE SMOKE DETECTORS LOOP 1 LOOP 2 FORWARD DETECTORS

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LOWER LOBE SMOKE DETECTORS

FROM SAMPLING PORTS

LOOP 1 LOOP 2 LOOP 1

TO VENTURI EJECTOR

MAIN DECK SMOKE DETECTORS B767-3S2F

LOOP 1 LOOP 2

ZONED


LOOP 2 AFT DETECTORS

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MAIN DECK CARGO COMPARTMENT SMOKE DETECTION FUNCTIONAL DESCRIPTION Purpose The test/alarm interface module (TAIM) consolidates the signal inputs from the six pairs of main deck smoke detectors. Two separate and identical sections support a dual loop configuration.

A system test is conducted by pressing the ENG/APU/CARGO fire test switch, or from the TAIM front panel test switches. As far as the TAIM is concerned, there is no difference in the source of the test input. The TAIM operates in AND logic during a test. During a system test, all detectors must signal an alarm before the alarm will be transmitted to the AFOLTS card. If a faulty smoke detector is found during test, the TAIM unit does not output an alarm signal to AFOLTS for that loop, and AFOLTS gives a status/maintenance message to EICAS MAIN CARGO LOOP 1 (2). If two loops are inoperative, the FIRE/OVHT SYS message shows.

Component Location The TAIM is in the main equipment center attached to the inboard side of the E3 rack. Physical Description The module has twelve indicator lamps (LEDs), a lamp test switch and two loop test switches. Functional Description The main deck smoke detectors operate the same way as the smoke detectors for the lower cargo compartment. A single AFOLTS card serves the main deck smoke detectors. The AFOLTS card logic remains unchanged. Signals to and from the 12 main deck smoke detectors go through the test/ alarm interface module (TAIM) The TAIM has two separate and identical sections to support dual loop configurations. Each half of the TAIM unit is seen by the AFOLTS card as one smoke detector. The TAIM consolidates the 12 inputs (6 per loop) from the main deck smoke detectors into two inputs (1 per loop). This allows the AFOLTS card to look at signals from any main deck smoke detector as being from loop 1 or loop 2. During normal operation, the TAIM operates in OR logic. Any one of the six detectors that comprises main deck loop 1 or loop 2 may send an alarm signal to AFOLTS. For example, when loop 1 detects smoke in Zone A, the TAIM outputs a loop 1 alarm signal. Therefore, when loop 2 Zone C senses smoke, a second alarm signal also goes to AFOLTS.

Anytime a detector fails a test, that detector loop annunciation on EICAS and AFOLTS configures to single loop operation. Failed individual smoke detectors can be found by doing a test of the TAIM.

A 28V DC R BUS MAIN CARGO FIRE DETECTION ALTN PWR-MAIN CARGO

REGULATION PHOTO DIODE

LED

28V DC BAT. BUS

ENG/APU CARGO TEST

MAIN CARGO FIRE DETECTION-1

LIGHT OUTPUT REGULATOR

TEST

B

SYS FAIL LT RESET

MAIN CARGO FIRE DETECTION-2 M2027 MAIN DECK SMOKE DETECTOR LOOP 1 ZONE A

P11 PANEL

FAIL RESET

LOOP 1 TEST

DET E

DET D

MANUAL DET C TEST

M10445 FIRE/OVHT TEST PANEL (P8)

DET B

MAIN CARGO FIRE "A"

MAIN CARGO FIRE 2

FIRE/OVHT SYSTEM "C"

SYS FAIL LT

MN CARGO LP 1 "S & M"

MN CARGO LP 1 SMOKE DETECTOR TEST FOR MAIN CARGO COMPARTMENT LOOP 1

PRESS TO TEST LAMPS

MAIN

MD&T

M10445 FIRE/OVHT TEST PANEL (P8)

LOOP 1 ALARM DET F

MD&T

MN CARGO LP 2

MN CARGO LP 2 "S & M"

SYS FAIL LT RESET SYS TEST DET 1 FIRE

(L/R) EICAS COMPUTERS

DET 1 TEST 1F

1E

1D

1C

1B

1A

PRESS TO TEST

2F

2E

A

2D

2C

2B

B

2A

28V DC DET 1 28V DC DET 2 DET 2 FIRE

LOOP 2

DET 2 TEST

*INSTRUCTIONS*

MD&T

1. PRESS LAMP TEST VERIFY ALL INDICATORS ILLUMINATE.

FIRE

MAIN CARGO FIRE 1

2. PRESS AND HOLD TEST SWITCH FOR LOOP UNDER TEST. 3. VERIFY SIX INDICATORS ILLUMINATE, IF DETECTOR IS FAILED, INDICATOR WILL NOT ILLUMINATE.

A HALF

DISCRETE WARNING DISPLAY (P1)

4. RELEASE LOOP TEST SWITCH.

M2039 TEST ALARM INTERFACE MODULE MANUAL TEST

M2026 FIRE/OVERHEAT LOGIC TEST CARD

LOOP 2 TEST LOOP 2 ALARM

DET F

DET E

DET D

DET C

DET B

DET A

MAIN DECK CARGO COMPARTMENT SMOKE DETECTION - FUNCTIONAL DESCRIPTION B767-3S2F Page - 99

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LOWER CARGO FIRE EXTINGUISHING - INTRODUCTION

releases its contents immediately, and bottles 2 and 2A start a metered release that continues until the bottles are empty.

Purpose

If you push the discharge switch in flight, bottle 1 releases its contents immediately, and bottles 2 and 2A start to release their contents 30 minutes after bottle 1.

The lower cargo fire extinguishing system extinguishes fires in the forward or aft lower cargo compartments. Physical Description The lower cargo fire extinguishing system has these components: • • • • • • •

Fire extinguishing dump bottle 1 Fire extinguishing metered bottles 2 and 2A Three manifold pressure switches Two regulators Two filter/dryers Six non-metered discharge nozzles Five metered discharge nozzles

The fire extinguishing bottles contain halon 1301 fire extinguishing agent pressurized with nitrogen. Tubes connect the bottles to discharge nozzles in the cargo compartment ceiling and sidewall. Operation In the flight compartment, cargo fire arm switches set the discharge to the forward or aft compartment. The discharge switch starts the fire bottle discharge sequence. A line pressure switch puts on the DISCH indication to show the start of the discharge sequence. The dump bottle releases its contents into the selected compartment when you push the discharge switch. The bottle releases its contents quickly to extinguish the fire. After a time delay, the metered bottles release their contents slowly and at a controlled rate through the filter, dryer, and regulator units. Halon from the metered bottles replaces the extinguishing agent in the cargo compartment to keep the fire extinguished for 180 minutes. The fire extinguisher bottles operate differently in flight than on the ground. If the airplane is on the ground when you push the discharge switch, bottle 1

APU FIRE EXTINGUISHER BOTTLES CARGO COMPARTMENT FIRE EXTINGUISHER BOTTLES FORWARD CARGO COMPARTMENT (REF)

ENGINE FIRE EXTINGUISHER BOTTLES

LOWER CARGO FIRE EXTINGUISHING - INTRODUCTION B767-3S2F Page - 101

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LOWER CARGO COMPARTMENT - GENERAL DESCRIPTION Flight Compartment The flight compartment has a control panel to arm and operate the cargo fire extinguishing bottles to release the bottle contents into the forward or aft cargo compartment. Lower Forward Cargo Compartment The lower cargo fire extinguishing system uses these components to extinguish fires in one or the other lower cargo compartment: • • • •

Fire extinguishing bottles (3) Filter/dryers (2) Manifold pressure switches Regulators (2)

TO DISCH INDICATION CIRCUIT 2A FWD COMPT

2

1

UNMETERED OUTLET NOZZLE

TEMP COMPENSATED LOW PRESSURE SWITCHES CARGO COMPT SIDEWALLS CARGO AFT COMPT DOOR

CARGO DOOR MANIFOLD PRESSURE SWITCHES

METERED OUTLET NOZZLE

BULK CARGO DOOR (REF) TO AFT COMPT METERING NOZZLES

TO FWD COMPT METERING NOZZLES

FILTER/DRYER

REGULATOR

TO AFT COMPT UNMETERED NOZZLES

TO FWD COMPT UNMETERED NOZZLES LOW PRESSURE SWITCH BOTTLE 2

CARGO FIRE

BOTTLE 1 80 LB HALON

SQUIB

ARMED FWD

ARMED

80 LB HALON


AFT

2

A R M

33 LB HALON

BOTTLE 1 MANIFOLD PRESSURE SWITCH

DEPR DISCH

ARMED MAIN

MAIN

BOTTLE 2A DISCHARGE TUBING

BOTTLE 2 MANIFOLD PRESSURE SWITCHES

LOWER CARGO COMPARTMENT - GENERAL DESCRIPTION B767-3S2F Page - 103

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DISCH 1

A

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LOWER CARGO FIRE EXTINGUISHING - EXTINGUISHING BOTTLES Location The bottles are on the right side of the forward lower cargo compartment behind the cargo compartment lining. You release the velcro and lift the lining up for access. Physical Description The bottles contain Halon 1301 fire extinguishing agent pressurized with nitrogen. Bottle 1 (dump) has 80 pounds of Halon. Bottle 2 (metered) has 92 pounds of Halon. Bottle 2A (metered) has 33 pounds of Halon. Each bottle has a nitrogen charge at a pressure of 360 psi. The fire extinguishing bottles have these components: • Safety relief and fill port • Pressure switch • Discharge assemblies Indications Status messages, maintenance messages, and the DISCH light on the P61 panel show if the bottle pressure is low. Functional Description The discharge assembly has an explosive squib that releases the Halon through the discharge port. The pressure switch monitors the pressure in the bottle and is normally open. When the bottle pressure decreases, the switch closes and sends a signal. The safety relief and fill port is one fitting on the bottle. The safety relief opens to make sure the bottle does not break if internal pressure is too high.

Filter/Dryer and Regulator Assemblies A filter/dryer assembly and a regulator assembly are in the metering systems of the forward and aft cargo compartments. The filter/dryer cleans and dries the extinguishing agent. You must replace the filter/dryers after their use. The regulator controls the rate of discharge for bottle 2 and 2A. Training Information Point You cannot fill an empty bottle on the airplane. You must replace the bottle. You can weigh the bottles to find the empty/full condition.

WARNING: BE CAREFUL WHEN DISCONNECTING THE HOSE ASSEMBLY FROM THE FIRE EXTINGUISHER BOTTLE. IF THE FIRE EXTINGUISHING BOTTLE IS DISCHARGED, THE TUBING MAY BE PRESSURIZED. RELEASING THE PRESSURE COULD CAUSE INJURY.

WARNING: DO NOT TOUCH THE SQUIB BEFORE DOING THE PROCEDURE FOR DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE THE FIRE BOTTLE TO RELEASE ITS CONTENTS SUDDENLY AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

WARNING: BE CAREFUL WHEN YOU MOVE THE FIRE EXTINGUISHING BOTTLE. THE FIRE EXTINGUISHING BOTTLE IS HIGHLY PRESSURIZED AND HAS AN EXPLOSIVE CARTRIDGE AS A COMPONENT. ACCIDENTAL DISCHARGE OF THE FIRE EXTINGUISHING BOTTLE CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

THERMAL RELIEF VALVE

PRESSURE SWITCH 2A

2

1

THERMAL RELIEF VALVE DISCHARGE PORT

DISCHARGE PORT

PRESSURE SWITCH DISCHARGE PORT DISCHARGE SQUIB

DISCHARGE SQUIB

LOWER CARGO FIRE EXTINGUISHING - EXTINGUISHING BOTTLES B767-3S2F Page - 105

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LOWER CARGO FIRE EXTINGUISHING - EXTINGUISHING BOTTLES (CONT) Tests You must remove the fire extinguishing bottle each five years for a hydrostatic test. The date of the last test is on the bottle. You can do a check of the low pressure switch on the ground. One person must push the button on the low pressure switch housing while a second person monitors the DISCH light on the P8 control stand and the EICAS advisory message. If the DISCH light comes on, the low pressure switch operates correctly. The light goes off when you release the button.

THERMAL RELIEF VALVE

PRESSURE SWITCH 2A

2

1

THERMAL RELIEF VALVE DISCHARGE PORT

DISCHARGE PORT

PRESSURE SWITCH DISCHARGE PORT DISCHARGE SQUIB

LOWER CARGO FIRE EXTINGUISHING - EXTINGUISHING BOTTLES (CONT) B767-3S2F Page - 107

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FUNCTIONAL DESCRIPTION BOTTLE DISCHARGE Cargo Fire Switches When the FWD ARMED switch is pressed, the following occurs: • • • •

FWD cargo compartment heat valves close. Fire warning bell is silenced. FWD Squib test function is disabled. FWD Cargo Air Conditioning shuts down

When the AFT ARMED switch is pressed, the following occurs: • • • •

Aft and bulk cargo compartment heat valves close. Fire warning bell is silenced. AFT squib test function disabled. The air conditioning packs switch to high flow mode.

Cargo Fire Switches The cargo fire switch-lights have these functions: • Compartment fire indication • Enables cargo fire bottle squib operation circuit and gives a circuit ARMED indication Bottle Discharge Switch The bottle discharge switch has two functions, bottle discharge indication and squib operation of the cargo bottles. When a fire shows in one of the cargo compartments (the red annunciator light in the cargo fire switch is on), you push the cargo fire switch to ARM the discharge circuit. You then push the discharge switch to operate the squib on bottle 1. If the airplane is on the ground, metered bottles 2 and 2A immediately release their contents. If the airplane is in the air, metered bottles 2 and 2A release their contents after 30 minutes. A bottle discharge indication shows by a pressure switch on the bottle or a pressure switch in the discharge line. You must manually do a reset of the pressure switches in the discharge line after the extinguishing system operates.

To do a test of the pressure switch on the bottle and the discharge indication circuit, you operate the test switch on the bottle pressure switch.

28V DC HOT BAT BUS CARGO FEXT BTL 1 P6 MN PWR DISTR

3 25 PSI

A

K1 R

4

R

P

1 FWD

FWD CARGO COMPT SMOKE DETECTION

FWD CARGO FEXT DISCH LINE PRESS SW

AIR

A

W

GND SYS NO. 2 AIR GND RLY

W

2

ARMED

>300 PSI

B

FWD CARGO SQUIB LWR CARGO COMPT BTL 1

B T D

28V DC HOT BAT BUS CARGO FEXT BTL 2

30 MIN FWD COMPT BTL 2A LOCK-IN RLY DISCH RLY

FWD CARGO FIRE SW A

3

1

A

R MISC ELEC EQUIP PNL (P37) 4

DISCH

CARGO BTL 1

P

25 PSI FWD CARGO METERED DISCH LINE PRESS SW 4 P

CARGO BTL 2

BTL DISCH SW 1 2

MD&T INSTR LTS

3

MUST PUSH TO RESET

EICAS COMPUTER ADVISORY MSG

FWD CARGO SQUIB

APU/CARGO FIRE CONTROL (P8) 4 PUSH TO TEST

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>300 PSI

FWD CARGO SQUIB LWR CARGO LWR CARGO COMPT BTL 2A COMPT BTL 2 NOTE: FWD CARGO COMPARTMENT SHOWN, AFT IS SIMILAR

K2

FUNCTIONAL DESCRIPTION BOTTLE DISCHARGE B767-3S2F

>300 PSI


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BOTTLE 2 AND 2A DISCHARGE CIRCUIT - FUNCTIONAL DESCRIPTION Bottle Discharge Circuit for Bottles 2 and 2A After you push the discharge switch, the squib on bottle 1 operates, and the fwd compartment lock-in relay energizes. Bottle 1 releases its contents immediately. Bottles 2 and 2A start a metered discharge immediately if the airplane is on the ground. If the airplane is in the air, the metered discharge starts after a 30minute delay. A bottle discharge indication shows by a pressure switch on the bottle or a pressure switch in the discharge line. You must manually do a reset of the pressure switches in the discharge line after the extinguishing system operates. To do a test of the bottle pressure switches and the discharge indication circuit, you push the test buttons on the bottle pressure switches.

25 PSI FWD CARGO COMPT SMOKE DETECTION

R

R

A

1 K1 W

28V DC HOT BAT BUS C773 CARGO FEXT BTL 2

SYS 2 AIR GND RLY

W

B

2

ARMED

C


C T D

3 FWD CARGO FIRE SW A

A

CARGO BTL 1

P

P

>300 PSI

>300 PSI

CARGO BTL 2 K2 EICAS COMPUTER ADVISORY MSG

MD&T

2

INSTR LT

3

INPUTS TO PUT OFF RECIRC FANS, CARGO HEAT, FWD GALLEY CHILLER, AND FWD/MID GALLEY PWR

APU/CARGO FIRE CONT (P8)

FWD CARGO SQUIB LWR CARGO COMPT BTL 2A

EFF - ALL

B


NOTE: FWD CARGO COMPARTMENT SHOWS, AFT IS SIMILAR

BOTTLE 2 AND 2A DISCHARGE CIRCUIT - FUNCTIONAL DESCRIPTION 5/20/13

FWD CARGO METERED DISCH LINE PRESS SW

R MISC ELEC EQUIP PNL (P37)

1

DISCH

ATA 26-00

25 PSI

30 MIN FWD COMPT BTL 2A LOCK-IN RLY DISCH RLY

1

Page - 111

>300 PSI

A

BTL DISCH SW

B767-3S2F

P

GND

FWD

28V DC HOT BAT BUS C781 CARGO FEXT BTL 1 P6 MN PWR DISTR

FWD CARGO FEXT DISCH LINE PRESS SW

AIR


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FIRE PROTECTION - OPERATIONAL TEST

APU Squib.

General

To do a test of the squib on the APU fire extinguishing bottle, you push the TEST 1 squib test switch on the P61 panel.

The operational tests for the fire extinguishing system are cargo squibs and engine and APU squibs. You can do a squib continuity test of all bottles from the squib test panel. The squib test panel is on the P61 panel. Cargo Squibs The cargo squib test supplies current to the squibs on the cargo compartment fire extinguisher bottles. Squib test switches on P61 give an easy test of all six squibs, two on each bottle. Power is from the 28v dc hot battery bus. This test makes sure there are no open circuits in the cargo compartment fire extinguishing squibs and the related wiring. Green lights show squib circuit continuity. The squib operates with 3.5 amps. The test current is 50 ma. The voltage drop across the test lamp does not let enough current flow to fire the squib. You must make sure the replacement lamps are the correct type and value. Accidental squib operation and bottle content release can occur. Engine Squibs The engine squib test supplies current to the squibs for the two engine fire extinguishing bottles. You push these two switches on the P61 panel to do a test of the squibs: TEST 1 - does a test of the two squibs on bottle 1 TEST 2 - does a test of the two squibs on bottle 2 A successful test shows when the ENG L and R green lights come on.

ENG BTL 1 DISCH

L ENG OVHT

ENG BTL 2 DISCH

DISCH 1

1

2

L E F T

ENG 1 BOTTLE

R ENG OVHT

ENG 2 BOTTLE

DISCH 2

ALL MESSAGES ARE ADVISORIES ENG BTL 1 (C) ENG BTL 2 (C)

R I G H T

CARGO BTL 1 (C) CARGO BTL 2 (C) APU BTL (C)

ENG FIRE CONTROL PANEL (P8) CARGO BOTTLE 2

CARGO BOTTLE 1 APU FIRE WARNING HORN

CARGO BOTTLE 2A

EICAS

AIR

APU FIRE

SQUIB TEST

GND 30-MIN DELAY

FIRE BOTTLE ARMED

BOTTLE DISCHARGED

ENG L

R

1

2

TEST 1

APU

CARGO 2A

TEST 1 FWD TEST 2 AFT

2


APU SHUTDOWN

SQUIB TEST PANEL (P61) CARGO FIRE ARMED

FLIGHT DECK CALL

FWD FLIGHT INPH

SERVICE INPH

EMER EXIT WHEELWELL LT TEST RS LIGHTS OFF

ARMED

LS


AFT

REMOTE APU CONTROL PANEL (P40)

A R M

DEPR

APU BTL DISCH

APU BOTTLE

DISCH

APU

DISCH

ARMED MAIN

MAIN

APU/CARGO FIRE CONTROL PANEL

FIRE PROTECTION - OPERATIONAL TEST B767-3S2F Page - 113

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WHEEL WELL FIRE DETECTION - INTRODUCTION Purpose The wheel well is protected from an overheat condition caused by hot landing gear brakes or tire fires. Physical Description Each element has a nickel wire around it and insulating material contained in the steel tube. The insulating material is heat sensitive and becomes more conductive when the temperature increases. Location The detector is a single loop detector on the ceiling of the wheel well bay. Two sensors in series are attached to the top of each main wheel well.

SINGLE LOOP WHEEL WELL FIRE DETECTORS

WHEEL WELL FIRE DETECTION - INTRODUCTION B767-3S2F Page - 115

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WHEEL WELL FIRE DETECTION - GENERAL DESCRIPTION General Two sensor loops are in the top of each main wheel well. The wheel well fire detector is a single Loop Fenwal detection system. A signal from any wheel well fire detector element goes to the duct leak and wheel well fire card in the P54 fire protection card file. The card causes flight compartment indications of a wheel well fire. You do a test of the wheel well fire detection system from a test switch on the fire/overheat test panel on P8.

WARNING CAUTION

AURAL WARNING SPEAKER (WARNING)

P7 FIRE

CONFIG

PULL UP

A/P DISC


WHEEL WELL FIRE (A)

EICAS DISPLAY UNIT (P2) BELL/CHIME AURAL & MASTER WARNING MODULES WARNING ELECTRONICS UNIT (P51)


DUCT LEAK & WHEEL WELL FIRE CARD

D O O R S

BRAKE TEMP WHL WELL FIRE

TAIL SKID

LEFT TO GA CLB

1

NOSE

G E A R

RIGHT

2

TEMP SEL



ENG/APU CARGO

UP

CON CRZ

SYS FAIL LEADING EDGE

TEST FAIL P-RESET

TRAILING EDGE OFF

FIRE/OVERHEAT TEST PANEL (P8) WHEEL WELL FIRE DET LOOP

B767-3S2F Page - 117

P3-1

WHEEL WELL FIRE DETECTION - GENERAL DESCRIPTION ATA 26-00

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RETRACT 270K

B767-3S2F Page - 118

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WHEEL WELL FIRE DETECTION - FUNCTIONAL DESCRIPTION General When there is a fire and the temperature along a detector gets to 400F (204C), the resistance between the nickel wire and the grounded steel tube decreases. The duct leak and wheel well fire card in the P54 card file senses this decrease. The card gives the flight compartment indications of a wheel well fire. Operation of the wheel well test switch makes a ground for each detector loop and does a check of the continuity of the detection circuit. If the circuit has continuity, wheel well indications show. A fault (short circuit) gives the same indications as a wheel well fire.

115V AC STBY BUS WW FIRE DUCT LEAK

DET CKT

WARNING ELECTRONICS UNIT

P11 WHEEL WELL FIRE

DUCT LEAK AND WHEEL WELL FIRE CONTROL CARD (P54)

L/R EICAS COMPUTER (E8)

WHEEL WELL TEST (P8)

RIGHT WHEEL RIGHT WHEEL WELL DET WELL DET ELEM SENSOR ELEM SENSOR

1/16 INCH

STEEL TUBE OUTER (GROUNDED) CONDUCTOR

MD&T

FIRE

CENTRAL CONDUCTOR

P1 LEFT WHEEL LEFT WHEEL WELL DET WELL DET ELEM SENSOR ELEM SENSOR

CONNECTOR EACH END

WHL WELL FIRE

MD&T HEAT SENSITIVE ELECTRICALLY CONDUCTIVE MATERIAL

P3

28V DC BAT BUS WW FIRE IND/TEST

WHEEL WELL FIRE IND (P37)

P11

DUCT LEAK DETECTION SENSOR (TYPICAL)

WHEEL WELL FIRE DETECTION - FUNCTIONAL DESCRIPTION B767-3S2F Page - 119

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WING AND BODY DUCT LEAK DETECTION - INTRODUCTION Purpose The detector loop finds an increase in temperature around the pneumatic duct. Physical Description The duct leak detector is a Fenwal type detector with thermistor material in the tube. The detector has two conductors. The center conductor connects to the detector card, and the outer conductor (detector case) connects to airplane ground. The temperature sensitive thermistor material is between the two conductors. The wing duct leak detectors and body duct leak detectors are similar. Location The detector loop is parallel to the pneumatic ducts from the engine strut to wing joint to the left or right isolation valve and between the left and right isolation valves. The loop is also on the body pneumatic duct from the center isolation valve to the APU shutoff valve.

WING DUCT LEAK DETECTORS

BODY DUCT LEAK DETECTORS

WING DUCT LEAK DETECTORS

WING AND BODY DUCT LEAK DETECTION - INTRODUCTION B767-3S2F Page - 121

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WING AND BODY DUCT LEAK DETECTION - DETECTORS Purpose Wing duct leak detectors monitor the pneumatic distribution ducts in the wing leading edges into the air conditioning compartments to the left and right isolation valves. The body duct leak detectors extend from the center isolation valve to the APU fire wall. Physical Description The wing and body detection sensors (elements) are in a single loop circuit. Each element has a nickel wire and insulating material contained in a steel tube. The insulating material is heat sensitive and becomes more conductive with a temperature increase.

1/16 INCH OUTER CONDUCTOR (GROUNDED) CENTRAL CONDUCTOR OUTER CONDUCTOR (GROUNDED)

HEAT SENSITIVE ELECTRICALLY CONDUCTIVE MATERIAL CONNECTOR EACH END DUCT LEAK DETECTION SENSOR (TYPICAL) WING AND BODY DUCT LEAK DETECTION - DETECTORS B767-3S2F Page - 123

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WING AND BODY DUCT LEAK DETECTOR - FUNCTIONAL DESCRIPTION General When a segment of a duct leak detector gets to the overheat temperature, an alarm signal goes to the detection circuit on the duct leak overheat and wheel well fire card in the P54 card file. The detection circuit receives the signal and makes an alarm signal to put on the DUCT LEAK light on the P5 panel and the caution messages on EICAS in the flight compartment. When the duct leak detector decreases to the reset temperature, the alarm signal stops. Training Information Point The duct leak test switch connects a ground for each detector loop and does a check of the continuity of the detection circuit. If the circuit has continuity, duct leak indications show. A fault (short circuit to ground) gives the same indication as overheat condition. The test only operates on the ground.

115V AC STBY BUS

MD&T

DUCT LEAK

MD&T

DUCT LEAK

MD&T

DUCT LEAK

DET CKT

WW FIRE DUCT LEAK P11 PANEL

(R WING)

WING BLEED DUCT DETECTORS - RIGHT

(R WING ENG STRUT) DET CKT

WING BLEED DUCT (L WING) DETECTORS - LEFT

DUCT LEAK

OFF DUCT LEAK

DET CKT

DUCT LEAK AND WHEEL WELL FIRE CARD (P54)

R BLD DUCT LEAK L BLD DUCT LEAK BODY DUCT LEAK L/R EICAS CMPTR

60 40

L ISLN

DUCT LEAK TEST

(FUSELAGE (AFT (ADP TAIL) CARGO COMPT) COMPT)

GND SYS 1 AIR/GND (P36)

WING AND BODY DUCT LEAK DETECTOR - FUNCTIONAL DESCRIPTION Page - 125

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R ISLN VALVE

V A L V E

DUCT LEAK

DL UE CA TK

O F F

DUCT LEAK BLEED

ADP APU

L ENG

AIR

B767-3S2F

0

C ISLN

OVHT

TEST PANEL (P61)

DUCT PRESS PSI

20

VALVE

BLEED

(L WHEEL WELL)

80

R L

(L WING ENG STRUT)

V A L V E

BLEED AIR SUPPLY (P5)

OVHT

R ENG O F F

B767-3S2F Page - 126

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WING AND BODY DUCT LEAK DETECTION - STRUT OVERHEAT DETECTORS Purpose The strut overheat thermal switches monitor the temperature in the engine strut. A leak in the pneumatic duct causes an overheat condition. Physical Description The strut overheat detectors are thermal switches that connect in a series configuration. The switch connects a ground when the temperature gets to a set level. Location There are two strut overheat thermal switches in each engine strut adjacent to the PRSOV.

SWITCH

WING AND BODY DUCT LEAK DETECTION - STRUT OVERHEAT DETECTORS B767-3S2F Page - 127

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THERMAL MATERIAL

B767-3S2F Page - 128

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STRUT OVERHEAT DETECTORS - FUNCTIONAL DESCRIPTION Functional Description When the temperature in the strut gets to a preset value, the strut thermal switch closes and gives an input to the bleed air control card. If the input signal is still there after a five-second time delay, the card latches and gives an output. Output 1 shows the duct leak annunciator light on P5. Output 2 sends the EICAS message, L/R STRUT DUCT LEAK. In the pneumatic system, the bleed air control card commands the high pressure shutoff valve and pressure regulating valve to close. This stops engine bleed air. If the pressure regulating valve or high pressure shutoff valve fails to close, the bleed annunciator light on the air supply panel comes on and the EICAS message of L/R ENG PRV or L/R ENG HPSOV shows. To reset the system, cycle the engine bleed air supply switch.

28V DC R BUS R AIR SUPPLY ENG BLEED CONT

PWR SPLY 5 SEC

OFF

RESET

28V DC R BUS R AIR SUPPLY ENG BLEED CONT

ON L ENG BLD AIR SPLY BLEED AIR SPLY PNL (P5)

PWR SPLY

RESET

P11 CB PANEL ON R ENG BLD AIR SPLY BLEED AIR SPLY PNL (P5)

ALARM 1 1

LATCH RESET ALARM 2

MD&T

DUCT LEAK

MD&T

DUCT LEAK

L BLEED AIR CONTROL PC

5 SEC

OFF

V

V

BLEED AIR SUPPLY (P5) ALARM 1 1

LATCH RESET ALARM 2

R BLEED AIR CONTROL PC

L STRUT DCT LEAK B R STRUT DCT LEAK B L/R EICAS CMPTR (E8)

ELECTRICAL SYSTEM CARD FILE (P50)

DUCT LEAK DET SNSR DUCT LEAK DET SNSR

K143 SYS 1 AIR/GND (P36)

DUCT LEAK DET SNSR L WING ENGINE STRUT

STRUT LEAK OFF FUEL QTY TEST PANEL (P61)

1

GND

DUCT LEAK DET SNSR R WING ENGINE STRUT

SENDS CLOSE COMMAND TO HIGH PRESSURE SHUTOFF VLV AND PRESSURE REGULATING VLV. TO RESET, CYCLE BLEED SW FAILURE OF PRV OR HPSOV TO CLOSE SHOWS BY BLD LT AND RESPECTIVE ENG PRV FAIL OR ENG BLD VAL EICAS MESSAGE

STRUT OVERHEAT DETECTORS - FUNCTIONAL DESCRIPTION B767-3S2F Page - 129

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B767-3S2F Page - 130

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WING AND BODY DUCT LEAK DETECTION & INTRODUCTION Purpose The wing and body duct leak detection system monitors the pneumatic ducts from the APU to the center isolation valve and the engine ducts from the bleed valve to the left or right isolation valve for leaks. The detection of a leak shows on the pneumatic panel and makes an EICAS CAUTION message. Purpose The detector loop finds an increase in temperature around the pneumatic duct.

60

L ISLN

R L

40

80 DUCT PRESS PSI

20

0

R ISLN

VALVE

VALVE

C ISLN V A L V E

DUCT LEAK BLEED

DL UE CA TK

OVHT

DUCT LEAK BLEED

APU

L ENG

R ENG

V A L V E

O F F

WING DETECTOR SENSOR LOOPS

OVHT

ADP

O F F

AIR SUPPLY PANEL (P5)

BODY DETECTION SENSOR LOOP

L BLD DUCT LEAK R BLD DUCT LEAK BODY DUCT LEAK L STRUT DCT LEAK R STRUT DCT LEAK

EICAS DISPLAY (CAUTION LEVEL B)

B767-3S2F Page - 131

FIRE PROTECTION CARD FILE (P54)

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ELECTRICAL SYSTEM CARD FILE (P50)


B767 ATA 26 Student Book

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