Sistemas Diversos

Treinamento de Manutenção Familiarização em Sistemas Diversos

Boeing 737-600/700/800/900

Linhas aéreas Inteligentes

7

Training Manual

NOTICE

THIS MANUAL HAS BEEN PREPARED FOR AIRPLANES SYSTEM

TRAINING. IT WILL NOT BE REVISED AND DOES NOT AMEND OR SUPERSEDE INFORMATION CONTAINED IN APPLICABLE GOVERNMENTAL REGULATIONS AND BOEINGS APPLICABLE SERVICE

BULLETINS, MAINTENANCE MANUALS, OVERHAUL MANUALS AND WRITTEN INSTRUCTIONS.


737-600/700/800/900 Familiarization Manual Maintenance Training


EFFECTIVITY YB202 30-00-00

Page 1 Oct 2003

Ice and Rain Protection Systems

TABLE OF CONTENTS SUBJECT

CHAPTER SECTION SUBJECT

PAGE

ICE AND RAIN PROTECTION – INTRODUCTION ............................................................................................................................................... 30-00-00.............. 02 GENERAL DESCRIPTION..................................................................................................................................................................................... 30-00-00.............. 04 WTAI – INTRODUCTION ....................................................................................................................................................................................... 30-11-00.............. 06 COMPONENT LOCATION..................................................................................................................................................................................... 30-11-00.............. 08 ANTI-ICE PANEL.................................................................................................................................................................................................... 30-11-00.............. 10 INLET COWL ANTI-ICING SYSTEM – INTRODUCTION...................................................................................................................................... 30-20-00.............. 12 CONTROLS............................................................................................................................................................................................................ 30-20-00.............. 14 PITOT AND STATIC – INTRODUCTION............................................................................................................................................................... 30-30-00.............. 16 WINDOW / PITOT HEAT MODULE ....................................................................................................................................................................... 30-30-00.............. 18 CONTROL CABIN – INTRODUCTION .................................................................................................................................................................. 30-41-00.............. 20 WINDOW HEAT CONTROL UNIT – BITE ............................................................................................................................................................. 30-41-00.............. 22 WINDSHIELD WIPER SYSTEM – INTRODUCTION............................................................................................................................................. 30-42-00.............. 26 WATER LINES – INTRODUCTION........................................................................................................................................................................ 30-71-00.............. 28



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ICE AND RAIN PROTECTION - INTRODUCTION Purpose The ice and rain protection system keeps ice from these airplane parts:

− Wing leading edges − Engine inlet cowls − Air data probes − Flight compartment windows − Water and waste system lines and drains.

Abbreviations and Acronyms

− CTAI - cowl thermal anti-ice − TAI - thermal anti-ice − WHCU - window heat control unit − WTAI - wing thermal anti-ice



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ICE AND RAIN PROTECTION – GENERAL DESCRIPTION Wing and Inlet Cowl Thermal Anti-ice Systems The wing thermal anti-ice and the engine inlet cowl thermal anti-ice systems use hot bleed air to prevent ice. Air Data Probe Heat The air data probes use electric heat to prevent ice. Flight Compartment Windows Flight deck windows use electric heat to do these functions:

− Prevent ice formation on the windows − Prevent fog on the windows − Improve window impact strength.

The windows use these features to improve forward vision in rain:

− Wipers − Hydrophobic (rain repellent) coatings.

Water and Waste System lines and Drains The water and waste lines and drains use electric heat to prevent ice.

Ice and Rain Controls The controls and indications for the ice and rain protection systems are in the flight compartment on the P5 forward overhead panel.



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ICE AND RAIN PROTECTION – WTAI – INTRODUCTION Purpose The wing thermal anti-ice system (WTAI) keeps ice from the leading edge of the wing. General Description The WTAI system uses hot air from the pneumatic system to heat the three inboard leading edge slats of the wing. A switch on the P5 forward overhead panel controls the operation of the WTAI system. The WTAI system may operate in flight or on the ground. When the system is on, the valves open and hot air from the pneumatic ducts goes to the leading edge of the wings. The heated air flows to the three inboard leading edge slat spray tubes. The air sprays into the slat cavities and exhausts overboard through holes in the bottom of the slats. Overheat switches in each wing leading edge, protect the slats from overheat. This overheat protection operates only when the airplane is on the ground. Switches on the control stand close the WTAI valves when you advance the engine thrust levers. This conserves engine thrust for takeoff. This thrust conservation protection only operates when the airplane is on the ground.

The air/ground logic gives the wing anti-ice system air ground sense feedback. The engine and wing anti-ice module uses this feedback to enable overheat and thrust conservation protection for the wing anti-ice system. It also turns off the WTAI system during takeoff.



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ICE AND RAIN PROTECTION – WTAI – COMPONENT LOCATION Flight Compartment The engine and wing anti-ice control panel is on the P5 forward overhead panel. Forward Equipment Compartment There are two control stand anti-ice switches. They are on the autothrottle switchpacks. The switchpacks are in the forward equipment compartment. Engine There are two WTAI solenoid valves. They are on the top of the engine compressor case. Wing Leading Edges There are two WTAI shutoff valves. They are in the wing leading edges, outboard of each engine strut. There are two WTAI ground overheat thermal switches, They are on the WTAI duct in the wing leading edges downstream of the WTAI valves. The WTAI supply ducts are on the forward wing spars. There are six WTAI telescoping ducts. They are in the wing leading edges. There are six WTAI spray tubes. They are in the three inboard slats of each wing.



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ICE AND RAIN PROTECTION – WTAI – ANTI-ICE PANEL Purpose The anti-ice panel does these things:

− Gives the flight crew interface with the wing and engine inlet cowl anti-icing systems

− Has the circuitry for control and indication of the wing anti-icing system

− Has the circuitry for control and indication of the engine inlet cowl anti-icing systems.

Location The panel is on the P5 forward overhead panel. General Description The wing anti-ice valve is open when the wing ant-ice switch is in the ON position. The blue VALVE OPEN light monitors the valve and switch positions. These are the light indications:

− Light is off - the switch is in the OFF position and the valve is closed

− Light is dim - the switch is in the ON position and the valve is open

− Light is bright - the switch position and valve position disagree or the valve is in transit.



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ICE AND RAIN PROTECTION – INLET COWL ANTI-ICING SYSTEM – INTRODUCTION Purpose The inlet cowl anti-icing system keeps ice from forming on the engine inlet cowl. General Description Each engine has an inlet cowl anti-icing system. The systems operate in flight and on the ground. A switch on the P5 forward overhead panel controls the operation of each inlet cowl anti-icing system. When the system is on, the inlet cowl thermal anti-ice (TAI) valve opens. Hot air from the engine bleed air interstage duct goes through the valve into the hollow inlet cowl. The warm air increases the temperature in the inlet cowl. The warm air then goes overboard through a vent at the bottom of the cowl. Each engine is the source of its inlet cowl thermal anti-icing air. Thermal anti-icing air is from the engine bleed air interstage duct, upstream of the pressure regulator and shutoff valve. An inlet cowl TAI pressure switch monitors the pressure in the duct downstream of the inlet cowl anti-icing valve.



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ICE AND RAIN PROTECTION – INLET COWL ANTI-ICING SYSTEM – CONTROLS Purpose The anti-ice panel does these things:

− Gives the flight crew interface with the wing and engine inlet cowl anti-icing systems

− Has the circuitry for control and indication of the cowl anti-icing system.

Location The panel is on the P5 forward overhead panel. General Description The cowl anti-ice valve opens when the switch is in the ON position on the ground or in flight. The blue COWL VALVE OPEN light shows the valve and switch positions. These are the light indications:

− Light is off - the switch is in the OFF position and the valve is closed

− Light is dim - the switch is in the ON position and the valve is open

− Light is bright - the switch position and valve position are not the same or the valve is in transit.

When the duct pressure downstream of the valve is too high, this is the indication:

− Amber COWL ANTI-ICE light − MASTER CAUTION and ANTI-ICE annunciator lights.



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ICE AND RAIN PROTECTION – PITOT AND STATIC – INTRODUCTION Purpose The probe anti-icing system prevents ice on the air data probes. General You control the probe heat from the window/pitot heat module on the P5 forward overhead panel. The probes have integral heaters that use electrical power for heat. The probe anti-icing system supplies heat to these probes:

− Angle of attack sensor (2) − Total air temperature probe − Pitot probes (5).

The static system sense ports are not part of the probe heat system. These ports are flush with the fuselage and heat is not necessary.



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ICE AND RAIN PROTECTION – PITOT AND STATIC – WINDOW / PITOT HEAT MODULE Purpose The window/pitot heat module does these things:

− Controls the electric power to the probe anti-icing systems − Gives the flight crew indication of the probe anti-icing

system status. Location The window/pitot heat module is on the P5 forward overhead panel. General Description There are two air data probe heater systems, A and B. These toggle switches let the crew turn on the probe heat systems:

− PROBE HEAT A − PROBE HEAT B.

There are two system indication light banks, one for the A system and one for the B system. The lights come on when the probe heaters do not draw electrical current.



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ICE AND RAIN PROTECTION – CONTROL CABIN – INTRODUCTION Purpose The control cabin window anti-icing system improves window impact strength and prevents ice formation on the flight compartment windows. General Description The control cabin anti-icing system uses electrical power to heat the flight compartment windows. The controls and indications for the control cabin window anti-icing system are on the P5 overhead panel. Window heat control units (WHCUs) are part of the control cabin window anti-icing system. The WHCUs do these things:

− Monitor window temperatures − Supply ON and OVERHEAT system indication − Do system tests − Program power output to the windows.

The WHCUs control power to these windows:

− No. 1 left and right − No. 2 left and right.

Thermal switches monitor window temperature and control power to these windows:

− No. 4 left and right − No. 5 left and right.

Windows in the thermal switch control systems are not part of the P5 overhead panel indication and test functions.



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ICE AND RAIN PROTECTION – CONTROL CABIN – WINDOW HEAT CONTROL UNIT – BITE THIS PAGE INTENTIONALLY LEFT BLANK



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ICE AND RAIN PROTECTION – CONTROL CABIN – WINDOW HEAT CONTROL UNIT – BITE Purpose The WHCUs have front face BITE that isolates system faults to the LRU interface level. General Description The BITE circuitry detects failures in these:

− WHCU internal faults − Window − Temperature sensor − Control power input − Bus power input − Associated wiring.

The WHCU has a 10-register FAULT HISTORY memory storage capability. BITE Test Switches The WHCU has these switches:

− LAMP TEST − BIT VERIFY − FAULT HISTORY − BIT LAMP RESET.

The LAMP TEST switch does a test of the six BIT indicator lamps. This verifies power and indication availability. The BIT VERIFY switch starts a system self test. This does a check of system faults. The FAULT HISTORY switch shows the last 10 registers one register at a time. The BIT LAMP RESET switch clears the fault from the WHCU. BITE Indications The BIT TEST OK lamp shows that a BIT VERIFY test is complete and found no faults. The lamp stays on for 15 seconds. The WHCU has these red fault lamps:

− WHCU-LRU − WINDOW SENSOR − BUS POWER − WINDOW POWER − P5-9/CONTROL POWER.

The WHCU-LRU lamp shows a failure of the WHCU unit. The WINDOW SENSOR lamp shows a failed sensor due to opens, shorts, or wiring problems.



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ICE AND RAIN PROTECTION – CONTROL CABIN – WINDOW HEAT CONTROL UNIT – BITE The BUS POWER lamp shows that there is no power to the WCHU bus. The WINDOW POWER lamp shows that there is no window power or there is over current to the window. This is due to either a window, wiring, or a connector open or shorted problem. The P5-9/CONTROL POWER lamp shows that there is no power to the WHCU.



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ICE AND RAIN PROTECTION – WINDSHIELD WIPER SYSTEM – INTRODUCTION Purpose The windshield wiper system removes rain, sleet, and snow from the No. 1R and No. 1L flight compartment windows. General Two wiper control switches on the P5 forward overhead panel give the flight crew control of the system. The system has two windshield wiper and drive assemblies. Location The WIPER control switches are on the P5 forward overhead panel. The two windshield wiper assemblies are on the No. 1R and No. 1L flight compartment windows. The two windshield wiper drive assemblies are on the No. 1R and No. 1L window sills. You get access to the windshield wiper drive assemblies from under the P7 glareshield.



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ICE AND RAIN PROTECTION – WATER LINES – INTRODUCTION Purpose The water and toilet drain anti-ice system prevents ice formation in theses areas:

− Potable water system service and supply components − Gray water system drain components − Vacuum waste system drain and service components.

General It is important to prevent ice formation in the water and toilet systems. Ice formation in the systems can cause these problems:

− Ice expansion damage − Line blockage that prevents normal system operation − Line blockage that prevents normal service operations − Ice formations on the forward drain mast can break off

and damage airplane structure. The water and toilet drain anti-icing systems use electric power for heat. These system components have integral heaters:

− Service panel fittings − Drain masts − Hoses with integral heating elements.

Components without integral heaters get heat from these components:

− Heater tape (ribbon heaters) − Heater blankets.

Training Information Point The water and toilet drain anti-icing systems require electric power. If you park the airplane in freezing conditions with no electric power, drain the water and toilet systems to prevent ice formation. Pull the circuit breakers for the water tank compressor and water heaters before you drain the potable water system.



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EFFECTIVITY YB202

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Page 1 Oct 2003

Fire Protection



PAGE

FIRE PROTECTION – INTRODUCTION ............................................................................................................................................................... 26-00-00.............. 02 ENGINE FIRE DETECTION – INTRODUCTION ................................................................................................................................................... 26-11-00.............. 04 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-11-00.............. 06 ENGINE AND APU FIRE DETECTION MODULE ................................................................................................................................................. 26-11-00.............. 08 ENGINE FIRE EXTINGUISHING – INTRODUCTION ........................................................................................................................................... 26-21-00.............. 10 OPERATION........................................................................................................................................................................................................... 26-21-00.............. 12 APU FIRE DETECTION – INTRODUCTION.......................................................................................................................................................... 26-15-00.............. 14 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-15-00.............. 16 APU FIRE EXTINGUISHING – INTRODUCTION.................................................................................................................................................. 26-22-00.............. 18 OPERATION........................................................................................................................................................................................................... 26-22-00.............. 20 CARGO COMPARTMENT SMOKE DETECTION – INTRODUCTION ................................................................................................................. 26-16-00.............. 22 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-16-00.............. 24 COMPONENT LOCATION..................................................................................................................................................................................... 26-16-00.............. 26 SMOKE DETECTOR TEST.................................................................................................................................................................................... 26-16-00.............. 28 CARGO COMPARTMENT FIRE EXTINGUISHING – INTRODUCTION............................................................................................................... 26-23-00.............. 30 OPERATION........................................................................................................................................................................................................... 26-23-00.............. 32 LAVATORY SMOKE DETECTION – INTRODUCTION......................................................................................................................................... 26-14-00.............. 34 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-14-00.............. 36 LAVATORY FIRE EXTINGUISHING – LAVATORY FIRE EXTINGUISHING BOTTLE AND TEMPERATURE INDICATOR............................... 26-24-00.............. 38 WHEEL WELL OVERHEAT DETECTION – INTRODUCTION.............................................................................................................................. 26-17-00.............. 40 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-17-00.............. 42 COMPRATMENT OVERHEAT DETECTION CONTROLLER............................................................................................................................... 26-17-00.............. 44 WING AND BODY OVERHEAT DETECTION – INTRODUCTION........................................................................................................................ 26-18-00.............. 46 GENERAL DESCRIPTION..................................................................................................................................................................................... 26-18-00.............. 48 PORTABLE FIRE EXTINGUISHING...................................................................................................................................................................... 26-26-00.............. 50



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

− Fire − Smoke − Overheat − Pneumatic duct leaks.

Fire/Overheat Detection The airplane has these fire/overheat detection systems:

− Engine overheat detection − Engine fire detection − APU fire detection − Wheel well fire detection − Wing/Body overheat detection − Cargo compartment smoke detection − Lavatory smoke detection.

Extinguishing The airplane has these fire extinguishing systems:

− Engine − APU − Lavatory − Cargo compartment − Portable fire extinguishers.


− adv - advisory − APU - auxiliary power unit − BITE - built in test equipment − det - detector − DISP - display − E/E - electronic equipment − ENG - engine − ext - extinguish − hyd - hydraulic − inop - inoperable − LED - light emitting diodes − LOC - local − lts - lights − maint - maintenance − MD&T - master dim and test − mem - memory − MLG - main landing gear − ovht - overheat − PA - passenger address − ref - reference − rev - reverser − typ - typical − vlv - valve − warn - warning − W/W - wheel well



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FIRE PROTECTION - ENGINE FIRE DETECTION - INTRODUCTION Purpose The engine overheat and fire detection system uses detectors on the engine. The detectors monitor engines for overheat and fire conditions. When the system senses an overheat or a fire condition, alarm indications operate in the flight compartment. The indications are on the P7 glareshield panel and on the engine and APU fire control panel. A bell also operates in the flight compartment for an engine fire. The left flap position transmitter sends data to SMYD 2.



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FIRE PROTECTION - ENGINE FIRE DETECTION - GENERAL DESCRIPTION General Description These are the components for engine overheat and fire:

− Engine overheat/fire detector (loop A and loop B) − Engine and APU fire detection module − Glareshield, P7 panel − Engine and APU fire control panel − Aural warning unit.

Overheat/fire detectors on the engine send signals to the engine and APU fire detection module. This module will supply aural and visual indications in the flight compartment. The engine and APU fire detection module gives visual indications for detector faults on the module and the engine and APU fire control panel panel. Overheat/fire test You use the TEST switch on the engine and APU fire control panel. In the OVHT/FIRE position, the indications in the flight compartment are the same as for the real fire condition. If the test fails, use the engine and APU fire detection module to isolate the fault. NOTE: During the engine overheat/fire test, the APU fire and wheel

well fire circuits are also tested.

Fault/inop test You use the TEST switch on the engine and APU fire control panel. In the FAULT/INOP position, the indications in the flight compartment are the same as a real fault condition. If the test fails, use the engine and APU fire detection module to isolate the fault. NOTE: During engine fault test, the APU fire detector fault circuit is

tested. Single Loop Operation If an engine overheat/fire detector fails to operate, the engine and APU fire detection module automatically changes to single loop operation. In the single loop mode, only one loop must detect an overheat or fire condition for the engine and APU fire detection module to give the alarm condition. There is no indication in the flight compartment of single loop operation until you do the OVHT/FIRE test.



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FIRE PROTECTION - ENGINE FIRE DETECTION - ENGINE AND APU FIRE DETECTION MODULE Purpose The engine and APU fire detection module monitors detectors for overheat and fire conditions on the engine. Also it monitors for fire conditions on the APU. Physical Description The control circuits for the engine overheat and fire, and the APU fire detection are in the module. The front panel has these components:

− ENGINE 1 LOOP A amber fault light − ENGINE 1 LOOP B amber fault light − ENGINE 2 LOOP A amber fault light − ENGINE 2 LOOP B amber fault light − APU amber fault light − Three red FAULT DISPLAY lights − FAULT/INOP test switch.

Location The engine and APU fire detection module is on the electronic equipment compartment on the E2-2 shelf.

Operation During normal conditions, all front panel lights are off. When a fault condition occurs, the related FAULT AREA light comes on. The FAULT DISPLAY lights show a fault code. When you push the FAULT/INOP test switch, faults are simulated to do a check of the circuit ability to detect a fault. If the circuits operate correctly, all lights on the front panel come on. If a light does not come on, it shows a faulty circuit operation. The FAULT DISPLAY lights show the type of fault and the detector location. Fault Signal Priorities When there are multiple engine loop faults (two or more amber lights on), this is the display priority:

Highest Priority Engine 1 Loop A Engine 1 Loop B Engine 2 Loop A Engine 2 Loop B

Lowest Priority APU



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FIRE PROTECTION - ENGINE FIRE EXTINGUISHING - INTRODUCTION Purpose The engine fire extinguishing system puts out fires in the engine compartment. General Description The engine fire extinguishing system floods the engine compartments with halon to put out the fire. Two fire extinguisher bottles supply the halon to either engine. Physical Description These are the components of the engine fire extinguishing system:

− Engine and APU fire control panel − Fire extinguisher bottles (2) − Engine fire extinguishing ports.

Location The two engine fire extinguisher bottles are in the top left corner of the main wheel well. The engine and APU fire control panel is in the flight compartment on the P8 panel.



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FIRE PROTECTION - ENGINE FIRE EXTINGUISHING - OPERATION Operation When there is an overheat or fire condition, the fire handle switch for that engine unlocks. You can also use the handle switch override under the handle to unlock the fire handle switch. When you pull the switch up, the engine systems are shutdown and isolated for safety. Engine 1 Fire Extinguishing When you turn the engine 1 (left) fire handle switch clockwise, the extinguisher bottle squib 1 on the R bottle operates. This breaks a seal and sends the halon in the R bottle to engine 1. If you turn the same engine fire handle switch counter-clockwise, the extinguisher bottle squib 1 on the L bottle operates. This sends the halon in the L bottle to engine 1. When an engine fire extinguisher bottle is empty, the amber BOTTLE DISCHARGED light on the engine and APU fire control panel comes on. Engine 2 Fire Extinguishing The engine 2 (right) fire extinguishing system operates the same as engine 1. The engine 2 fire handle switch causes the squib 2 on the L or R bottle to operate.



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FIRE PROTECTION - APU FIRE DETECTION - INTRODUCTION Purpose The APU fire detection system uses detectors on the APU. The detectors monitor the APU for a fire condition. When the system senses a fire condition, alarm indications operate in the flight compartment. The indications are on the glareshield P7 panel and on the engine and APU fire control panel on the P8. A bell also operates in the flight compartment. A horn and a red light operate in the right main wheel well.



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FIRE PROTECTION - APU FIRE DETECTION - GENERAL DESCRIPTION General Description These are the components of the APU fire detection system:

− APU fire detectors − Engine and APU fire detection module − Glareshield, P7 panel − Engine and APU fire control panel − P28 APU ground control panel. − Aural warning unit − APU electronic control unit.

Fire detectors on the APU send signals to the engine and APU fire detection module. This module will supply aural and visual indications in the flight compartment. Also, the module sends signals to the APU control unit to automatically shutdown the APU. The APU ground control panel gives the external indications of an APU fire. A horn and red light operate alternately at a one per second rate. Overheat/Fire Test You use the TEST switch on the engine and APU fire control panel. In the OVHT/FIRE position, the indications in the flight compartment and on the APU ground control panel are the same as for a real fire condition. If the test fails, use the engine and APU fire detection module to isolate the fault.

Fault/Inop Test You use the TEST switch on the engine and APU fire control panel. In the FAULT/INOP position, the indications in the flight compartment are the same as a real fault condition. If the test fails, use the engine and APU fire detection module to isolate the fault.



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FIRE PROTECTION - APU FIRE EXTINGUISHING - INTRODUCTION Purpose The APU fire extinguishing system extinguishes fires in the APU compartment. General Description The APU fire extinguishing system floods the APU compartment with halon to extinguish the fire. One fire extinguisher bottle supplies the halon to the APU compartment. Physical Description These are the components of the APU fire extinguishing system:

− Engine and APU fire control panel − APU fire extinguishing bottle − APU ground control panel.

Location The APU fire extinguishing bottle is in the horizontal stabilizer accessory compartment. The engine and APU fire control panel is in the flight compartment on the P8 panel. The APU ground control panel is in the right main wheel well, on the aft bulkhead.



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FIRE PROTECTION - APU FIRE EXTINGUISHING - OPERATION Operation When there is a fire condition, the APU fire warning switch unlocks. You can also use the warning switch override under the handle to unlock the switch. When you pull the APU fire warning switch up, the APU systems are shutdown and isolated. When you turn the APU fire handle switch clockwise or counter-clockwise, the extinguisher bottle squib operates. This breaks the seal and lets the halon in the bottle to go to the APU compartment. You can also use the APU fire control panel to operate the APU fire extinguisher bottle. When the APU fire extinguisher bottle is empty, the amber APU BOTTLE DISCHARGED light on the engine and APU fire control panel comes on.



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FIRE PROTECTION - CARGO COMPARTMENT SMOKE DETECTION - INTRODUCTION Purpose The lower cargo compartment smoke detection system gives warnings in the flight deck if there is smoke in a lower cargo compartment. There are warnings for the forward and the aft lower cargo compartments. Abbreviations and Acronyms

− CEU - cargo electronic unit



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FIRE PROTECTION - CARGO COMPARTMENT SMOKE DETECTION - GENERAL DESCRIPTION General Description These are the components of the lower cargo compartment smoke detection system:

− Smoke detectors − Cargo electronic units − Cargo fire control panel − Aural warning unit − Fire warning lights.

The smoke detectors are in a dual loop configuration. Each smoke detector monitors the cargo compartment for smoke and heat. If the detector senses smoke or heat, a signal goes to the cargo electronic unit. The cargo electronic unit sends a signal to the flight compartment for indications. These are the indications in the flight compartment:

− FWD or AFT cargo fire light on the cargo fire control panel comes on

− P7 FIRE WARN lights come on − Bell sound from the aural warning unit.



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FIRE PROTECTION - CARGO COMPARTMENT SMOKE DETECTION - COMPONENT LOCATION Component Location The lower cargo compartments have many cargo smoke detectors and one cargo electronic unit in each compartment. The forward lower cargo compartment has four smoke detectors. The aft lower cargo compartment has six smoke detectors. The detectors are in the ceiling of the compartments. You remove a protective guard to get access to a smoke detector. One cargo electronic unit is in the ceiling on the left side of each cargo compartment, inboard of the cargo door. You remove a cover to get access to a cargo electronic unit.



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FIRE PROTECTION - CARGO COMPARTMENT SMOKE DETECTION - SMOKE DETECTOR TEST General The cargo smoke detection system uses these components:

− Cargo fire control panel − Two cargo electronic units (CEUs) − Smoke detectors.

Cargo Electronic Unit Test These are the indications if you push the LAMP TEST or PRESS TO TEST buttons:

− LAMP TEST, all 16 red lights come on − PRESS TO TEST, all 16 red lights come on.

At the same time, these show on the cargo fire control panel:

− The EXT FWD and EXT AFT green lights come on − FWD and AFT red switchlights come on − DISCH amber light comes on.

If there is a fault, one or more of the red lights do not come on. Cargo Fire Control Panel Test These are the indications when you push the TEST button on the cargo fire control panel:

− EXT FWD and EXT AFT green lights come on − FWD and AFT red switchlights come on − DISCH amber light come son − P7 FIRE WARN lights come on − Aural warning unit gives the bell sound.

At the same time, the 16 red lights on the CEU come on. If there is a fault, the DETECTOR FAULT light comes on. Training Information Point This table shows when the DETECTOR FAULT light comes on automatically.

STATUS DET SELECT SWITCH

DETECTOR FAULT LIGHT

Loop A and B fail

NORMAL ON

Loop A fail A ON Loop B fail B ON



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FIRE PROTECTION - CARGO COMPT FIRE EXTINGUISHING - INTRODUCTION Purpose The cargo compartment fire extinguishing system extinguishes fires in these cargo compartments.

− Forward − Aft.

General Description The lower cargo fire compartment extinguishing system has these components:

− Two fire extinguishing bottles. − Five discharge nozzles.

The fire extinguishing bottles contain halon 1301 fire extinguishing agent pressurized with nitrogen. Tubing connects the bottles to the discharge nozzles in the cargo compartment ceilings.



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FIRE PROTECTION - CARGO COMPT FIRE EXTINGUISHING - INTRODUCTION



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FIRE PROTECTION - CARGO COMPT FIRE EXTINGUISHING - OPERATION Operation To operate the cargo compartment fire extinguishing system you do these things:

− Push the related cargo fire warning switchlight − Lift the guard to the DISCH switchlight − Push the DISCH switchlight for a minimum of 1 second.

For more information on the cargo fire control panel, see cargo compartment smoke detection. (SECTION 26-16)



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FIRE PROTECTION - LAVATORY SMOKE DETECTION - INTRODUCTION Purpose The lavatory smoke detection system alerts the cabin crew to smoke conditions in the lavatories. A smoke detector is in the ceiling of each lavatory.



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FIRE PROTECTION - LAVATORY SMOKE DETECTION - GENERAL DESCRIPTION General The smoke detection system gives aural and visual alarm indications when smoke is detected in a lavatory. Interfaces The lavatory smoke detector has these interfaces:

− Electrical power. Electrical Power The smoke detection system uses 28v dc from bus 1.



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FIRE PROTECTION - LAVATORY FIRE EXTINGUISHING - LAV FIRE EXTING BOTTLE AND TEMP INDICATOR Purpose The lavatory fire extinguishing system extinguishes fires under the wash basin and trash bin area. Physical Description The lavatory extinguishing system has these components:

− Fire extinguisher bottle − Temperature indicators.

Location The lavatory fire extinguishing systems are in the lavatories under the wash basin. Operation The extinguisher bottle has two discharge ports. The ports have eutectic plugs. These plugs melt at high temperatures. When there is an overheat or fire condition, this occurs:

− Temperature indicators change color (white to black) − Eutectic plug melts − Extinguisher releases halon to stop the fire.

Training Information Point You must weigh the lavatory extinguisher bottle at regular intervals.



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FIRE PROTECTION - WHEEL WELL OVERHEAT DETECTION - INTRODUCTION Purpose The wheel well fire detection system uses overheat sensing elements in the main wheel well. It monitors the wheel well for fire condition. When the system senses a fire condition, alarm indications operate in the flight compartment. The indications are on the glareshield panel P7 and on the engine and APU fire control panel P8. A bell also operates in the flight compartment.



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FIRE PROTECTION - WHEEL WELL OVERHEAT DETECTION - GENERAL DESCRIPTION General Description These are the components for the wheel well fire detection:

− Main wheel well fire (overheat) sensing element − Compartment overheat detection controller − P7 glareshield panel − Engine and APU fire control panel − Aural warning unit.

Fire (overheat) sensing element in the main wheel well supplies the wheel well fire detection signal. The signal goes to the compartment overheat detection controller. This unit supplies the fire alarms. These are the flight compartment indications of a wheel well fire:

− Two red FIRE WARN lights on P7 panel come on − Bell sounds in the aural warning unit − Red WHEEL WELL light on engine and APU fire control

panel comes on. If the wheel well fire alarms come on due to a real fire or a fault, the MAINT ADV light on the compartment overheat detection controller comes on. Use the module to do a check for real alarm or a fault condition. You use the test switch on engine and APU fire control module panel to the OVHT/FIRE position to do a test of the wheel well

sensing element. If the test passes, the indications in the flight compartment are the same as for a real fire condition. If the test fails, use the compartment overheat detection controller to isolate the fault. NOTE: During the wheel well fire test, the engine overheat, the engine

fire, and the APU fire systems also do a test.



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FIRE PROTECTION - WHEEL WELL OVERHEAT DETECTION - COMPARTMENT OVERHEAT DETECTION CONTROLLER Purpose The compartment overheat detection controller monitors sensing elements for overheat and fire conditions in the wheel well and the wing and body areas. Physical Description The control circuits for the wing and body overheat detection are in the controller. The front panel has these components:

− MAINT ADV (maintenance advisory) light − LED display − BITE instructions − Four BITE control switches (MEM READ, MEM CLEAR,

LOC TEST and DISP TEST). Location The compartment overheat detection controller is in the electronic equipment compartment on the E1-4 rack. BITE Test Switches and Indications The non-volatile memory provides a storage area for ten fault/alarms. Failure of the control cards, power supply card, loss of ac or dc power are not stored. These failures are coded 00 to 05. Short circuit faults are stored as alarm codes.

MEM READ (memory read switch), accesses the non-volatile memory. MEM CLEAR (memory clear switch), clears the non-volatile memory. The existing faults and alarms can not be cleared until corrected. LOC TEST (local test switch), initiates a test sequence of the control circuits and detector elements. This test will display codes 00 to 05, open loop codes and short loop codes. DISP TEST (display test switch), verifies correct operation of the control circuits. This is indicated by code 88 being displayed. MAINT ADV (maintenance advisory light), is on when a fault or an alarm is stored in the non-volatile memory. The light does not come on with codes 00 to 05.



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FIRE PROTECTION - WING AND BODY OVERHEAT DETECTION - INTRODUCTION Purpose The wing and body overheat detection system uses sensing elements adjacent to the pneumatic ducts. It monitors the pneumatic distribution system ducts for overheat conditions. When the system detects an overheat condition, alarm indications turn on in the flight compartment. The indications are on the P7 glareshield panel and on the P5 air conditioning/bleed air controls panel.



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Page 48 Oct 2003


FIRE PROTECTION - WING AND BODY OVERHEAT DETECTION - GENERAL DESCRIPTION General Description These are the major components of the wing and body overheat detection system:

− Wing/body overheat sensing elements − Compartment overheat detection controller − Air conditioning panel.

The wing and body overheat detection system uses a single overheat sensing loop. The detector loop in the left and right wing and body supplies overheat and fault signals to the compartment overheat detection controller. This controller uses the signals to give overheat or fault indications in the flight compartment on the air conditioning panel. The fault signals show on the compartment overheat detection module.

-



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FIRE PROTECTION - PORTABLE FIRE EXTINGUISHING Purpose There are portable fire extinguishers to extinguish fires inside the airplane. There are two types of extinguishers, water-type and halon. The water-type extinguishers are for solid combustible fires. The Halon extinguishers are for electrical and flammable liquid fires. Location There are extinguishers in these areas:

− Flight compartment − Galley − Passenger compartment.

Placards identify all of the extinguisher locations. Physical Description The water-type extinguishers contain a water and anti-freeze mixture. Each water extinguisher has these parts:

− Trigger (discharge valve) − Water cylinder − Handle with internal gas cartridge − Discharge nozzle − Quick-release mounting strap.

Each Halon extinguisher has these parts:

− Pressure indicator − Halon cylinder − Trigger − Discharge nozzle − Handle lock pin − Handle.

Operation To operate the water-type extinguisher, turn the handle and push the trigger. To operate the Halon extinguisher, remove the handle lock pin and push the handle. Training Information Point After you use the water-type extinguisher, you must fill it again and replace the cartridge. If the handle lock pin on the Halon extinguisher is not there, you must weigh the extinguisher to find if it is full. The pressure indicator is not a satisfactory check of the extinguisher.



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Page 52 Oct 2003

EFFECTIVITY YB202





Page 1 Oct 2003

Lights

TABLE OF CONTENTS

SUBJECT


PAGE

LIGHTS– INTRODUCTION .................................................................................................................................................................................... 33-00-00.............. 02 FLIGHT COMPARTMENT – INTRODUCTION...................................................................................................................................................... 33-10-00.............. 04 PASSANGER COMPARTMENT – INTRODUCTION ............................................................................................................................................ 33-20-00.............. 06 CONTROLS............................................................................................................................................................................................................ 33-20-00.............. 08 CARGO AND SERVICE COMPARTMENT LIGHTS – INTRODUCTION.............................................................................................................. 33-30-00.............. 10 EXTERIOR – INTRODUCTION.............................................................................................................................................................................. 33-40-00.............. 12 CONTROL SWITCHES .......................................................................................................................................................................................... 33-40-00.............. 14 EMERGENCY LIGHTING – INTRODUCTION....................................................................................................................................................... 33-50-00.............. 16 POWER SUPPLIES................................................................................................................................................................................................ 33-50-00.............. 18 FUNCTIONAL DESCRIPTION ............................................................................................................................................................................... 33-50-00.............. 20



Page 2 Oct 2003


LIGHTS - INTRODUCTION General These are the light systems on the airplane:

− Flight compartment lights − Passenger compartment lights − Cargo compartment lights − Service compartment lights − Exterior lights − Emergency lights.


− att - attendant − ac - alternating current − bat - battery − brt - bright − dc - direct current − EE - electronic equipment − gnd - ground − instr - instrument − lt(s) - light(s) − prim - primary − PSU - passenger service unit − svce - service − sw - switch − typ - typical − vari - variable

− xfmr - transformer − xfr - transfer



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Page 4 Oct 2003


LIGHTS - FLIGHT COMPARTMENT - INTRODUCTION Purpose These are the four types of flight compartment lights:

− Instrument and panel lights − Miscellaneous lights − Flight crew lights − Master dim and test.

The instrument and panel lights are for the flight compartment controls and panel indications. The miscellaneous lights supply general lighting to the flight compartment. These are the miscellaneous lights:

− Panel and control stand flood lights − Circuit breaker panel lights − Standby compass light − Dome lights.

The flight crew lights supply light for specific tasks. These are the flight crew lights:

− Reading lights − Map lights − Flight kit lights − Chart lights.

The master dim and test system controls the light for the system annunciator and indicator lights. General Description The dome lights supply general lighting for the flight compartment. The glareshield supplies background lighting for the pilots. Each instrument and instrument panel has lighting. The control stand gets light from an overhead floodlight. The circuit breaker panels get light from floodlights. There are lights for the standby compass and map lighting. The master dim and test switch can do these functions:

− Test the indicator and panel lights − Cause the indicator and panel lights to come on in the

bright or dim mode. The replacement lamps for the lights in the flight compartment are above the right number three window.



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Page 6 Oct 2003


LIGHTS - PASSENGER COMPARTMENT - INTRODUCTION Purpose The lights in the passenger compartment supply these functions:

− General light in the passenger cabin − Reading lights − Information lights for the passengers and attendants − Lights in the lavatories − Lights in the galleys.

The light system also lets the passenger call the attendants for aid. The passenger compartment lights has these subsystems:

− Window lights − Ceiling lights − Reading lights − Passenger signs − Lavatory lights and signs − Passenger and lavatory call lights − Attendant work lights − Galley lights − Entry lights.



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Page 8 Oct 2003


LIGHTS - PASSENGER COMPARTMENT - CONTROLS Purpose You control these passenger cabin lights from the forward and aft attendant panels:

− Ceiling − Window − Entry − Work − Emergency (aft panel only).

Location The P13 forward attendant panel is on the forward lavatory wall. The P14 aft attendant panel is on the aft lavatory wall.



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Page 10 Oct 2003


LIGHTS - CARGO AND SERVICE COMPARTMENT LIGHTS - INTRODUCTION Purpose The cargo and service compartment lights supply light to help maintenance personnel and ground crews. Location There are cargo compartments lights in the forward and aft cargo compartments. There are service lights in these areas:

− Forward equipment compartment − Electronic equipment compartment − Right air conditioning compartment − Left air conditioning compartment − Aft accessory compartment (section 48 interior) − APU compartment − Tail cone compartment.

There are wheel well lights in the nose and main wheel wells.



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LIGHTS - EXTERIOR - INTRODUCTION Purpose The exterior lights supply light for airplane identification, direction, and to aid in the safe operation of the airplane. These are the exterior lights on the airplane:

− Wing illumination − Landing lights − White anti-collision lights − Red anti-collision lights − White, red and green position lights − Taxi and runway turnoff lights − Logo lights.



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Page 14 Oct 2003


LIGHTS - EXTERIOR - CONTROL SWITCHES Purpose The exterior lighting control switches control the airplane external lights. Location The exterior lighting control switches are in the flight compartment on the lower edge of the P5 forward overhead panel. General Description These are the switches on the P5 that control the external lights:

− Landing (retractable and fixed) − Runway turnoff − Logo − Position − Anti-collision − Wing − Wheel well − Taxi.



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Page 16 Oct 2003


LIGHTS - EMERGENCY LIGHTING - INTRODUCTION Purpose The emergency lighting system puts lights on areas inside and outside of the airplane. The emergency lights also show the exit paths. The emergency lights operate at these times:

− When emergency light system is on − When there is a loss of airplane DC power and the P5

forward overhead panel emergency light switch is in the ARMED position.

Location Control switches are at these locations:

− P5 forward overhead panel in the flight compartment − P14 aft attendant panel.

General Description The emergency lighting system has these components:

− Exit signs − Aisle lights − Floor proximity lights − Slide lights − Power supplies.



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Page 18 Oct 2003


LIGHTS - EMERGENCY LIGHTS - POWER SUPPLIES Purpose The power supplies give power to internal and external emergency lights. Physical Description The power supplies have these components:

− Battery pack − Test switch − Electrical connector − Control logic and charging circuit.

Location The power supplies are at these locations:

− Behind the ceiling panels at the forward entry area − Behind the ceiling panels at the aft entry area − On the side structure, near the floor.

Training Information Point The battery packs can fully recharge in 90 minutes. A test switch on the assembly turns on all the lights in the battery pack zone for zone lamp test.



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Page 20 Oct 2003


LIGHTS - EMERGENCY LIGHTS - POWER SUPPLIES Operation You use the emergency exit light switch on the P5 forward overhead panel or the emergency exit switch on the attendant panel. These switches control the emergency lights. The emergency exit light switch on the P5 panel has these positions:

− ON - makes emergency lights come on − OFF - prevents automatic operation − ARM - prepares system for automatic operation.

The NOT ARMED and MASTER CAUTION lights are on when the emergency light switch on the P5 panel is in the ON or the OFF positions. The 28V DC bus 1 supplies power to these indication lights. The emergency exit switch on the attendant panel has two positions, ON and NORMAL. The ON position makes the emergency lights come on. The NORMAL position sets automatic operation. The attendant panel switch will cause the lights to come on even if the P5 switch is OFF. Functional Description The power supplies use 28v dc for their charge and control logic circuits. The charge circuits charge the battery packs when these conditions occur:

− P5 emergency exit light switch is in the OFF or ARM position

− 28v dc bus 1 has power

− Attendant panel emergency exit light switch is in the NORMAL position.

When the P5 switch is in the ARM position, the power supply makes the emergency lights come on when one of these conditions occur:

− Attendant panel emergency exit switch is in the ON position.

− 28v dc bus 1 power drops less than 12 volts. Training Information Point If you remove all power from the airplane, the P5 emergency exit light switch must be in the OFF position and the attendant switch in the NORM position. This prevents the emergency lights operation so the batteries do not discharge. Each power supply contains a battery test switch. If you push this switch, the emergency lights connected to its power supply circuit will come on for one minute. Each power supply provides power to its series of emergency lights. When a power supply voltage goes low, the emergency lights in that circuit go off. The emergency lights operate for more than 10 minutes. When the 28v dc bus 1 has power and the emergency light switches on the P5 panel and the attendant panel are not ON, the battery packs are on charge. The time to fully charge the battery packs depends on the time that the emergency lights were on.



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Page 22 Oct 2003

EFFECTIVITY YB202






Page 1 Oct 2003

Oxygen



PAGE

OXYGEN – INTRODUCTION................................................................................................................................................................................. 35-00-00.............. 02 CREW – GENERAL DESCRIPTION...................................................................................................................................................................... 35-10-00.............. 04 CREW – INTERFACE ............................................................................................................................................................................................ 35-10-00.............. 06 CREW – OXYGEN PANEL..................................................................................................................................................................................... 35-10-00.............. 08 PASSANGER – INTRODUCTION.......................................................................................................................................................................... 33-20-00.............. 10 PORTABLE – INTRODUCTION............................................................................................................................................................................. 33-30-00.............. 12



Page 2 Oct 2003


OXYGEN - INTRODUCTION Purpose The oxygen systems supply oxygen to the flight crew, cabin attendants, and passengers. Oxygen can be used for these reasons:

− Life sustaining oxygen if the plane depressurizes − Emergencies − First aid.

General Description The flight crew oxygen system operates independently of the other systems. It is a high pressure gaseous system. High pressure gaseous oxygen is in a cylinder in the EE compartment. The manifold supplies oxygen to the flight crew oxygen masks. The passenger oxygen system uses chemical oxygen generators. The generators are in the passenger service units (PSUs). Each chemical generator is separate, and supplies only its masks. The masks connect to the chemical generators by flexible tubes. Abbreviations and Acronyms

− C - Celsius − EE - electronic equipment − F - fahrenheit − F/O - first officer

− oxy - oxygen − pass - passenger − ASU - Aft attendant station − LSU - lavatory attendant station − pnl - panel − FCU - flow control unit − VAU - voltage averaging unit − PSU - passenger service unit − press - pressure − rly - relay − SCF - standard cubic feet.



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Page 4 Oct 2003


OXYGEN - CREW - GENERAL DESCRIPTION Purpose The flight crew oxygen system supplies the flight crew with low pressure gaseous oxygen. General Description High pressure gaseous oxygen is stored in a cylinder. Over pressure devices protect the cylinder. A green plastic discharge indication disk on the fuselage skin shows cylinder discharge from overpressure (when the disk is missing). A cylinder head assembly connects the cylinder to the airplane distribution system. The oxygen supply lines are made of seamless stainless steel tubing and use flareless fittings. The flight crew masks supply the oxygen to the crew. The masks have diluter-demand regulators and controls. The masks are modular, independently adjustable, and easy to put on. When cylinder pressure is too low for operational requirements, you replace it.

Location These system components are in the EE compartment:

− High pressure oxygen cylinder − Cylinder head assembly − Overpressure discharge tubing.

Training Information Point Oxygen system maintenance requires special care and cleanliness. Oxygen system maintenance personnel should know the special materials and procedures used in system servicing. Refer to chapter 12 of the maintenance manual for these materials and procedures. Keep oxygen systems clean and dry. Use approved cleaning materials. WARNING: DO NOT ALLOW OIL, GREASE, DIRT OR

OTHER FLAMMABLE MATERIALS TO TOUCH OXYGEN SYSTEM COMPONENTS. THESE MATERIALS WHEN EXPOSED TO PRESSURIZED OXYGEN CAN IGNITE AND CAUSE AN EXPLOSION. A FIRE OR EXPLOSION CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.



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Page 6 Oct 2003


OXYGEN - CREW - INTERFACE Purpose The flight crew oxygen system has these interfaces:

− System supply tubing − Pressure indication − Overpressure discharge and indication − Flight crew communications system − Shutoff valve.

System Plumbing The system plumbing has these components:

− Corrosion resistant, seamless, stainless steel tubing − Flareless fittings − Bayonet-type quick-disconnect connectors − Flexible silicon rubber hoses with braided sheathing.

Shutoff Valves A shutoff valve on the cylinder head opens or closes the cylinder to the supply system. Pressure Indication A mechanical pressure gage on the oxygen cylinder shows the cylinder pressure. The gage shows pressure regardless of the cylinder shutoff valve position.

A pressure transducer on the cylinder coupling supplies a signal to the pressure gage in the flight compartment. Overpressure Discharge and Indication A frangible (breakable) disk on the oxygen cylinder protects the cylinder from overpressure. If an overpressure condition breaks this disk, the oxygen will flow overboard. This flow will blow out a green indication disk on the airplane fuselage. The cylinder discharge works with the cylinder shutoff valve open or closed.



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Page 8 Oct 2003


OXYGEN - CREW - OXYGEN PANEL Purpose The oxygen panel shows the crew oxygen cylinder pressure. Physical Description The CREW/PASS OXYGEN indicator is round, lighted, and measures from 0 - 2000 psi. Location The oxygen panel is on the P5 aft overhead panel. Operational Displays The indicator shows crew oxygen cylinder pressure. Nominal cylinder pressure is 1850 psi at an ambient temperature of 70F (21C). Training Information Point The crew oxygen cylinder shutoff valve must be open to pressurize the cylinder coupling and show on the indicator. The battery switch must be ON to supply power to the indicator.



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Page 10 Oct 2003


OXYGEN - PASSENGER - INTRODUCTION Purpose The passenger oxygen system supplies emergency oxygen to the passengers and cabin attendants. Location Passenger oxygen generators, masks, firing pin mechanisms, and deployment door latch actuators are in these units:

− Passenger service units (PSUs) − Lavatory service units (LSUs) − Attendant service units (ASUs).

A guarded toggle switch for manual release of the passenger oxygen masks is on the P5 aft overhead panel. A pressure switch for automatic release of the passenger oxygen mask is in the J23 junction box in the EE compartment. General Description The passenger oxygen system uses chemical generators to make oxygen. Oxygen from the generators flows through flexible supply hoses to the passenger oxygen masks.

Passenger oxygen masks deploy electrically one of these two ways:

− Manually by the crew with a guarded toggle switch on the oxygen system control panel (P5)

− Automatically by operation of a pressure switch (14000 feet cabin altitude).

Operational Displays The PASS OXY ON light on the P5 aft overhead panel comes on when the passenger oxygen masks deploy.



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Page 12 Oct 2003


OXYGEN - PORTABLE - INTRODUCTION Purpose Portable oxygen cylinders are used for walk around first aid and sustaining purposes. Protective breathing equipment (PBE) supplies a crew member with a smoke hood and an air system for protection against smoke or toxic fumes. The PBEs protect the user during fire fighting operations. Location These are the locations where there is portable oxygen equipment:

− Exterior walls of windscreens, lavatories, and galleys − Placarded overhead stowage bins − Placarded storage units.

General Description Each portable oxygen cylinder is a separate system. The cylinder stores a supply of oxygen under high pressure (1800 psig at 70F (21C)). An indicator on the cylinder shows cylinder pressure (quantity of oxygen available). A shutoff valve on the cylinder head controls the flow of the high pressure oxygen to the cylinder head assembly. Cylinder head components regulate oxygen pressure and flow to the attached mask(s).

The portable oxygen cylinders have these features:

− Identifying and instructional placards − High pressure cylinder − Cylinder pressure gage − Shutoff valve − Cylinder head assembly − Mask − Carrying strap.

Each PBE is a separate system. The PBE has these features:

− Vacuum sealed storage container with identifying and instructional placards

− Loose fitting universal sized smoke hood with oronasal mask and breathing air system.

Interface The portable oxygen equipment is independent (separate) of the other aircraft systems. Standard outlet fittings (bayonet type) are used on the portable oxygen cylinders.



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Page 14 Oct 2003

EFFECTIVITY YB202





Page 1 Oct 2003

Water and Waste



PAGE

WATER AND WASTE – INTRODUCTION............................................................................................................................................................. 38-00-00.............. 02 POTABLE WATER – FUNCTIONAL DESCRIPTION ............................................................................................................................................ 26-10-00.............. 04 WATER QUANTITY INDICATION SYSTEM – INTRODUCTION.......................................................................................................................... 38-14-00.............. 08 WATER TANK PRESSURIZATION – INTRODUCTION........................................................................................................................................ 38-42-00.............. 10 WATER TANK PRESSURIZATION – FUNCTIONAL DESCRIPTION................................................................................................................... 38-42-00.............. 12 WASTE DISPOSAL – INTRODUCTION ................................................................................................................................................................ 38-30-00.............. 16 GRAY WATER SYSTEM – WASTE WATER SYSTEM......................................................................................................................................... 38-31-00.............. 18 VACUUM WASTE SYSTEM – INTRODUCTION................................................................................................................................................... 38-32-00.............. 20 VACUUM WASTE SYSTEM – FUNCTIONAL DESCRIPTION.............................................................................................................................. 38-32-00.............. 22 WASTE TANK QUANTITY INDICATION SYSTEM – INTRODUCTION................................................................................................................ 38-33-00.............. 26



Page 2 Oct 2003


WATER/WASTE - INTRODUCTION Purpose The water and waste system supplies potable water to the lavatories and galleys and removes sink and toilet waste. The water and waste system also removes rain water from the door sill areas. General Description The water and waste system has these subsystems:

− Potable water − Air supply − Waste disposal.

The potable water system supplies water to the lavatories and galleys. The air supply system pressurizes the water tank. The waste disposal system removes waste from the lavatories, galleys, and door sill drains. Abbreviations and Acronyms

− ac - alternating current − C - celsius − CLS - continuous level sensor − cont - control

− dc - direct current − E - empty − F - fahrenheit − F - filter − F - full − FCU - flush control unit − fwd - forward − H - heater − ind - indication − lav - lavatory − LCM - logic control module − LED - light emitting diode − PLS - point level sensor − psig - pounds per square inch, gauge − qty - quantity − ref - reference − S - switch − T - transmitter − TYP - typical



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WATER/WASTE - POTABLE WATER – FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK



Page 5 Oct 2003


WATER/WASTE - POTABLE WATER – FUNCTIONAL DESCRIPTION Functional Description The potable water system has one tank that holds potable water. You fill and drain the water tank at the water service panel. To fill the water tank, open the fill/overflow valve and add water through the potable water fill fitting until the water flows from the potable water drain port. The water tank supplies water to these locations:

− Galley faucets − Lavatory faucets − Lavatory toilets.

Each lavatory has a water supply shutoff valve. The water supply shutoff valve lets you isolate the water supply to the sink or to the toilet. The water supply shutoff valve also lets you isolate the sink and the toilet at the same time. The forward lavatory has a drain valve. The forward lavatory drain valve drains water from the forward water supply lines. A water heater in each lavatory increases the temperature of the water supplied to the hot water faucet. The water tank level sensor sends the water quantity data to a water quantity transmitter. The water quantity transmitter sends

the data to a water quantity indicator at the attendant panel. The water quantity indicator shows the level of water in the tank. To drain the potable water system, you open these valves:

− Water tank drain valve − Forward lavatory drain valve (forward lavatory only) − Lavatory water supply shutoff valves (one in each

lavatory). When you drain the potable water system, the water drains overboard through the forward and aft potable water drain ports. Training Information Point When you drain the potable water system, you must drain water from these two areas:

− Water service panel − Forward lavatory.

The water service panel lets you drain the water tank and aft supply lines. The forward lavatory has a drain valve that lets you drain the forward water supply lines. When you drain the potable water system, you must turn the water supply shutoff valves in each lavatory to the SUPPLY ON position. If you do not turn the water supply shutoff valve to the SUPPLY ON position, water will not drain from the toilet or lavatory faucets.



Page 6 Oct 2003


WATER/WASTE - POTABLE WATER – FUNCTIONAL DESCRIPTION WARNING: IF THE POTABLE WATER SYSTEM IS NOT

DRAINED AT A MINIMUM OF ONE TIME EACH THREE DAYS, THE GROWTH OF BACTERIA CAN OCCUR. IF BACTERIA GROWTH CONTINUES, AND YOU DRINK THE WATER, ILLNESS CAN OCCUR.

You must fully drain the potable water system before you add a disinfectant or when you park the airplane in cold weather. WARNING: SEAL THE CARGO COMPARTMENT WITH THE

LINING. OBEY THE INSTRUCTIONS IN THE SPECIFIED PROCEDURE WHEN YOU INSTALL THE LINING. IF YOU INSTALL THE LINING INCORRECTLY, SMOKE CAN GET INTO THE PASSENGER COMPARTMENT DURING A FIRE.

You must remove the cargo compartment lining to get access to some of the potable water system components. Make sure you correctly replace the lining when you are done.



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Page 8 Oct 2003


WATER/WASTE - WATER QUANTITY INDICATION SYSTEM - INTRODUCTION Purpose The water quantity indication system measures and shows the quantity of water in the water tank. General Description These are the water quantity indication system components:

− Water level sensor − Water quantity transmitter − Water quantity indicator.

The water level sensor is a copper mesh capacitance-type sensor that is a part of the water tank. The water level sensor is permanently bonded between the inner lining and the composite structure of the water tank. The water quantity transmitter uses the measurement signal from the sensor to calculate the water level. The water level shows at the attendant panel on the water quantity indicator. Abbreviations and Acronyms

− dc - direct current − E - empty − F - full

− LED - light emitting diode − REF - reference − T - transmitter



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Page 10 Oct 2003


WATER/WASTE - WATER TANK PRESSURIZATION - INTRODUCTION Purpose The water tank pressurization system pressurizes the potable water tank. General Description Pressure for the water tank comes from the pneumatic system or the air compressor. The water tank pressurization system has these functions:

− Controls the air pressure that goes into the water tank − Selects the source of the pressurized air − Prevents contamination from unwanted material in the air.


− AC - alternating current − fwd - forward − psig - pounds per square inch gage − ref - reference − S - switch − typ - typical − V - volts



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WATER/WASTE - WATER TANK PRESSURIZATION - FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK



Page 13 Oct 2003


WATER/WASTE - WATER TANK PRESSURIZATION - FUNCTIONAL DESCRIPTION General The water tank pressurization system uses pressurized air from the pneumatic system or the air compressor to pressurize the water tank. Pneumatic System The pneumatic system supplies pressurized air to the water tank when the pneumatic system is on. The pneumatic system supply line gets air from a tap on the pneumatic manifold forward of the APU check valve. An in-line air filter cleans the air in the pneumatic system supply line. A pressure regulator controls the pneumatic system supply line pressure to a maximum of 35 psig. Air Compressor The air compressor supplies pressurized air to the water tank when the pneumatic system is off and these conditions are true:

− Pressure in the water tank is less than 30 psig (pressure limit switch is closed)

− Water service panel door is closed (compressor cut-out switch is closed)

− 115v ac main bus 1 is on. The air compressor gets air from a muffler above the ceiling of the cargo compartment. An air filter at the inlet of the air compressor cleans the air in the air compressor supply line. The pressure limit switch opens and stops the operation of the air compressor when the air pressure in the water tank increases to 40 psig. When the pressure decreases to 30 psig, the pressure limit switch closes and the air compressor starts. Training Information Point WARNING: SEAL THE CARGO COMPARTMENT WITH THE

LINING. OBEY THE INSTRUCTIONS IN THE SPECIFIED PROCEDURE WHEN YOU INSTALL THE LINING. IF YOU INSTALL THE LINING INCORRECTLY, THE FIRE EXTINGUISHING AGENT OR SMOKE CAN GET INTO THE PASSENGER COMPARTMENT DURING A FIRE.

To get access to the water tank pressurization system components, you remove the cargo compartment lining. When you are done, you must replace and seal the cargo compartment lining.



Page 14 Oct 2003


WATER/WASTE - WATER TANK PRESSURIZATION - FUNCTIONAL DESCRIPTION WARNING: MAKE SURE THERE IS NO PRESSURE IN THE

PNEUMATIC PRESSURE LINES BEFORE YOU DISCONNECT THEM. THE HIGH PRESSURE/TEMPERATURE AIR IN THE LINES CAN CAUSE INJURY TO PERSONS.

Before you remove water tank pressurization system components, you must release the pressure from the system. You can open the fill/overflow valve to release the pressure from the pneumatic pressure lines. To open the fill/overflow valve, use the valve handle at the water service panel. To stop operation of the air compressor, open the water service panel.



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Page 16 Oct 2003


WATER/WASTE - WASTE DISPOSAL - INTRODUCTION Purpose The waste disposal system removes water from the lavatory and galley sinks, human waste from the lavatory toilets, and rain water from the door sills. General Description The waste disposal system has these subsystems:

− Gray water − Vacuum waste − Waste tank quantity indication.

Gray Water System The gray water comes from the lavatory and galley sinks, and from door sill drains at each entry and galley service door. The gray water from the sinks drains overboard through drain masts. The gray water from the door sills drains overboard through drain fittings. Vacuum Waste System The vacuum waste system removes human waste from the toilets. The waste material is held in a waste tank until servicing.

Waste Tank Quantity Indication System The waste tank quantity indication system measures and shows the level of waste in the waste tank. Abbreviations and Acronyms

− ac - alternating current − A/C - air conditioning − BIT - built in test − C - Celsius − dc - direct current − F - Fahrenheit − FCU - flush control unit − FWD - forward − GND - ground − LCM - logic control module − mm - millimeter − PSID - pounds per square inch differential − REF - reference − SEC - section − SYS - system − TYP - typical − v - volts



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Page 18 Oct 2003


W/W - GRAY WATER SYSTEM - WASTE WATER SYSTEM Purpose The waste water system collects the waste water from the lavatory and galley sinks and drains the waste water overboard through heated drain masts. The system also gives exhaust ventilation for the lavatories and galleys. General Description The waste water system has these components:

− Lavatory and galley sink drains − Lavatory and galley sink drain vents − Drain hoses and lines − Drain masts.

The waste water drains overboard through the drain masts when the airplane is on the ground and when the airplane is in the air. Electrical heaters in the drain masts prevent the drain masts from freezing.



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Page 20 Oct 2003


WATER/WASTE - VACUUM WASTE SYSTEM - INTRODUCTION Purpose The vacuum waste system removes human waste material from the toilets and holds it in the waste tank. General Description The vacuum toilet collects human waste. A flush cycle puts the waste material into the vacuum waste tubing. Cabin pressure pushes the material to the vacuum waste tank. There are two sources that cause low pressure (vacuum) in the tank:

− The vacuum blower − Cabin-to-ambient pressure differential.

The waste is kept in the waste tank until servicing. Servicing is done at the waste service panel. The vacuum waste system has these components:

− Toilet assembly − Waste tank − Liquid separator − Waste tank rinse nozzle − Waste tank rinse filter − Waste tank rinse fitting assembly − Waste drain valve assembly

− Waste drain ball valve − Drain line blockage removal valve − Vacuum check valve − Vacuum blower − Vacuum blower barometric switch.


− ac - alternating current − C - Celsius − dc - direct current − F - Fahrenheit − FCU - flush control unit − FWD - forward − LCM - logic control module − REF - reference − TYP - typical − v - volts



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WATER/WASTE - VACUUM WASTE SYSTEM - FUNCTIONAL DESCRIPTION Vacuum Toilet Assemblies Operation of the flush switch sends a signal to the flush control unit (FCU). The FCU opens the rinse valve to supply potable water to flush the toilet bowl. After 0.7 seconds, the FCU closes the rinse valve. Each rinse cycle uses eight ounces of potable water. The FCU then opens the flush valve for four seconds to let the toilet waste drain out of the toilet. The flush valve then closes. The anti-siphon valve prevents the vacuum waste system from siphoning water from the potable water system. The manual shutoff handle closes the manual shutoff valve. Waste Tank Assembly The waste tank collects the waste from the lavatory toilets. Differential pressure causes the toilet bowl contents to flow from the toilet to the waste tank. The vacuum blower or cabin differential pressure supplies the differential pressure for the waste tank. The vacuum check valve prevents the pull of ambient air in from the waste tank vent port by the vacuum blower. Waste System Servicing You service the waste tank from the waste service panel.

Attach the waste drain hose to the waste drain valve and open the waste drain ball valve. When the tank is empty, attach the rinse hose to the waste tank rinse fitting. Then pressurize the rinse water supply. Rinse water flows through the waste tank rinse filter and two rinse nozzles. The waste tank rinse nozzles spray water on the inside of the tank to clean the point level sensors and waste tank. Add chemical precharge after the waste tank is fully drained and flushed. The waste drain ball valve proximity switch stops the operation of the vacuum blower when the waste drain ball valve is open. You use the drain line blockage removal valve to remove a blockage in the waste tank drain line. Rinse water flows to the drain line elbow and pushes the blockage out of the drain line. Interfaces The FCU must receive an enable signal from the logic control module (LCM) to operate the toilet components. The LCM disables the FCU if the waste tank is full. The LCM monitors the two point level sensors to find if the waste tank is full.



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WATER/WASTE - VACUUM WASTE SYSTEM - FUNCTIONAL DESCRIPTION If the FCU is enabled, a flush cycle starts with the operation of the flush switch. The flush switch sends a signal to the FCU. The FCU then sends a signal to operate the vacuum blower for 15 seconds. The signal goes through the waste drain ball valve proximity switch and the vacuum blower barometric switch. The waste drain ball valve proximity switch and vacuum blower barometric switch must be closed for the vacuum blower to operate. The waste drain ball valve proximity switch is closed when the waste drain ball valve is closed. The barometric switch is closed when the airplane is below 16,000 feet. Training Information Point The waste tank must be flushed at each servicing interval. If the waste tank is not serviced correctly, unwanted waste material can collect on the point level sensors. The waste material on the point level sensors can cause a tank full signal and stop operation of the lavatory toilets. You should flush crushed ice down the toilets at regular intervals. The crushed ice will help to prevent unwanted material from collecting in the vacuum waste lines.

CAUTION: DO NOT USE ICE CUBES AS AN ALTERNATIVE TO THE CRUSHED ICE. ICE CUBES CAN CAUSE DAMAGE TO THE POINT LEVEL SENSORS IN THE WASTE TANK.

There is a clean-out fitting in the forward vacuum waste line. You can use the clean-out fitting to clean a blockage between the waste tank and the forward lavatory.



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WATER/WASTE - WASTE TANK QUANTITY INDICATION SYSTEM - INTRODUCTION Purpose The waste tank quantity indication system measures and shows the quantity of waste in the waste tank. General These components are in the waste tank quantity indication system:

− Waste tank point level sensor (2) − Waste tank continuous level sensor − Logic control module (LCM) − Waste quantity indicator.

The waste tank quantity indication system does these functions:

− Monitors and shows the level of waste in the waste tank − Stops operation of the toilets when the waste tank is full − Gives indication when the lavatories stop operation for

waste tank full condition − Gives indication when the sensors are dirty − BIT.


− ac - alternating current − BIT - built in test − C - Celsius − dc - direct current − F - Fahrenheit − FCU - flush control unit − FWD - forward − LCM - logic control module − mm - millimeter − REF - reference − TYP - typical − v - volts



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EFFECTIVITY YB202





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Equipment and Furnishing



PAGE

EQUIPMENT / FURNISHING – INTRODUCTION ................................................................................................................................................. 25-00-00.............. 02 FLIGHT COMPARTMENT – CAPTAIN / FIRST OFFICER SEATS....................................................................................................................... 25-10-00.............. 04 PASSENGER COMPARTMENT – INTRODUCTION ............................................................................................................................................ 25-20-00.............. 08 BUFFET / GALLEY – INTRODUCTION................................................................................................................................................................. 25-30-00.............. 10 GALLEY POWER – FUNCTIONAL DESCRIPTION .............................................................................................................................................. 25-30-00.............. 12 LAVATORIES – INTRODUCTION ......................................................................................................................................................................... 25-40-00.............. 14 CARGO COMPARTMENTS – INTRODUCTION ................................................................................................................................................... 25-50-00.............. 16 FORWARD CARGO – ACCESS PANEL ............................................................................................................................................................... 25-50-00.............. 18 EMERGENCY EQUIPMENT – INTRODUCTION .................................................................................................................................................. 25-60-00.............. 20 OVERWING ESCAPE STRAPS............................................................................................................................................................................. 25-60-00.............. 22 ESCAPE LANYARDS............................................................................................................................................................................................. 25-60-00.............. 24 EMERGENCY LOCATOR TRANSMITTERS......................................................................................................................................................... 25-60-00.............. 26 DETACHABLE, FLIGHT COMPARTMENT............................................................................................................................................................ 25-60-00.............. 28 DETACHABLE, PASSENGER COMPARTMENT.................................................................................................................................................. 25-60-00.............. 30 ESCAPE SLIDES ................................................................................................................................................................................................... 25-60-00.............. 32



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EQUIPMENT/FURNISHINGS – INTRODUCTION Purpose The equipment and furnishings supply these things to the passengers and crew of an airplane:

− Comfort − Convenience − Safety − Cargo storage.

General Description ATA chapter 25, Equipment and Furnishings, includes these sections:

− Flight Compartment − Passenger Compartment − Buffet/Galley − Lavatories − Cargo Compartments − Emergency Equipment.


− AC - alternating current − APU - auxiliary power unit − ASU - attendant service unit − ATA - air transport association − DC - direct current − fwd - forward − LSU - lavatory service unit − PSIG - pounds per square inch gage − PSU - passenger service unit − RTV - room temperature vulcanizing rubber − typ - typical − VHF - very high frequency



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EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT - CAPTAIN/FIRST OFFICER SEATS Purpose The captain and first officer seats provide adjustable seats for the flight crew. Physical Description The seats are left or right hand (captain or first officer) and operate the same. The seat base has controls and mechanisms for seat fore/aft position. The controls are on the inboard side of each seat. The upper seat has controls and mechanisms for these adjustments:

− Seat height − Thigh pad position − Seat recline − Armrest height and stowage − Back cushion (lumbar support) position − Headrest position.

Four bogie units hold the base to the aircraft seat tracks. Rollers in each bogie unit make adjustment of the seat position easy. A spring-loaded track lock mechanism sets fore and aft movement on the seat tracks.

The aft end of each seat track curves outboard. This allows the seats to move outboard in the last five inches of travel. Seat Height The seat height lock mechanism controls seat height. To raise the seat, pull the height lock lever to unlock the seat height lock mechanism. Then lift your body weight to raise the seat. Release the height lock lever to lock the seat in position. To lower the seat, pull the height lock lever to unlock the seat height lock mechanism. Then lower your body weight into the seat. When the seat is at the desired level, release the height lock lever. Seat Fore and Aft Position The track lock mechanism controls seat fore and aft position. Pull the track lock lever towards the rear of the seat to unlock the track lock pin from the track. Then move the seat fore or aft as necessary. Release the track lock lever to lock the seat in position. Thigh Pad Position Turn the thigh pad adjustment handwheel to raise or lower the thigh pads.



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EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT - CAPTAIN/FIRST OFFICER SEATS NOTE: When you use the foot controls, pressure on the thigh

pad overrides the position of the thigh pad and allows the thigh pads to move. When you release pressure on the foot controls, the thigh pads return to their pre-set position.

Seat Recline To increase the recline angle, pull up and hold the seatback recline control lever then push aft on the seat back. Release the control lever to lock the seat back in the new position. To decrease the recline angle, pull up and hold the seatback recline control lever, then lean forward so that no pressure is on the seat back. Release the control lever to lock the seat back in the new position. Armrest Height and Stowage Armrest height adjustment knobs are under the forward end of the armrests. Turn the knob to move the armrest up or down. To store the armrest, lift up on the front of the armrest. When the armrest is up as far as it will go, you can push it in toward the center of the seat. Back Cushion (Lumbar Support) Position Two handwheels, one on each side of the seat, control the position of the back cushion. The handwheel on the left side

controls the up/down movement, the right handwheel controls the in/out movement. Headrest Position To adjust the headrest, move the headrest cushion to the right and turn it to select one of eight possible lock positions. Training Information Point Flexible hook and loop fastener tape secures the seat covers to the seat. You can remove the seat covers to clean them. Do operational checks with a person in the seat (170 pounds minimum weight). To remove the flight crew seats, you must first remove stops on the inboard seat tracks. Then slide the seats forward off the tracks.



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EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT - INTRODUCTION Purpose Flight compartment equipment/furnishings provide for the safety and comfort of the captain, first officer, and observers. General Description Flight compartment equipment/furnishings include these items:

− Flight crew seats − Furnishings at each crew station − Instrument panels − Circuit breaker panels − Glareshield − Linings − Insulation − Drip pan − Emergency equipment − Miscellaneous equipment.



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EQUIPMENT/FURNISHINGS - BUFFET/GALLEY - INTRODUCTION Purpose Galleys provide food and beverage preparation facilities. Location The airline determines the number and location of the galleys. There are seven possible galley locations. General Description Galleys may have different inserts. These are the typical galley inserts:

− Chiller − Oven − Refrigerator − Coffee maker − Sink − Storage − Waste container − Serving carts.

The galley has these connections:

− Structural support connections − Electrical power connections − Water and drain connections − Ventilation connections.

Installation Each galley bolts to the airplane structure. A tie rod with a quick-disconnect fitting attaches the top of the galley to the airplane structure. Floor fittings attach the bottom of the galley to the airplane structure. Floor Covering Floor covering in the galley installation areas consists of vinyl mats. There is a liquid barrier under the vinyl mat to prevent floor structural damage. Power Three-phase, 115V AC power from the number 1 and 2 generator buses energize the galleys. Engine-driven generators, the APU, or external power energizes the generator buses. The galley switch on the P5 overhead panel controls electrical power to the galleys. In order to preserve power for critical systems, all galley power will be lost automatically if a generator bus loses power.



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EQUIPMENT/FURNISHINGS - GALLEY POWER - FUNCTIONAL DESCRIPTION Functional Description The galley power supply is controlled by the galley power switch on the P5 forward overhead panel. When the galley switch is in the ON position, relays R603 and R604 energize. When the relays are energized, the galleys have power. Electrical load shedding happens if APU has high EGT, or overcurrent condition is detected in the electrical supply system from APU or engine generators. The overcurrent protection logic deenergizes relays R603 and R604 and there is no power supply to the galleys. Training Information Point See the electrical power chapter for more information on electrical load shedding. (CHAPTER 24)



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EQUIPMENT/FURNISHINGS - LAVATORIES - INTRODUCTION General Description The lavatories are modular, self contained units. Each lavatory has this equipment:

− Air sickness bag and sanitary napkin dispenser − Ashtray (interior and exterior) − Assist handle − Attendant call button and reset switch − Coat hook − Diaper changing table (some installations) − Dual roll toilet paper holder − Facial tissue dispenser − Fire extinguisher (in waste compartment) − Flushing toilet, with toilet seat and cover − Non-glass mirror (shatter resistant) − Handicap assist rails (some installations) − Information and instruction placards (including NO

SMOKING sign) − Light switches − Oxygen masks (2) − Paper cup dispenser − Public address system loudspeaker − Removable waste container − RETURN TO SEAT sign − Shaver outlet, 115v ac, 60 Hz (some installations) − Smoke detector (in the ceiling) − Soap dispensers

− Toilet seat cover dispenser − Wash basin with a stopper, faucet, and counter assembly − Water heater.

A lock with a safety-release lever is in each lavatory door. When a person in the lavatory locks the door, an OCCUPIED sign appears on an indicator on the passenger compartment side of the door. You may unlock this door from the passenger compartment side of the door without the use of special tools. The service unit provides lavatory ventilation. Air exhausts through overboard vents in each lavatory. The potable water system supplies water to the sink. The lavatory floor is of watertight fiberglass construction to prevent corrosion. A non-skid vinyl mat is bonded to the floor. Location The airline determines the number and location of the lavatories. There are eight possible lavatory locations. Training Information Point Lavatory modules bolt to floor brackets and attach to overhead structure with adjustable tie rods. When you install a lavatory, adjust the length of the tie rod to fit without preload.



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EQUIPMENT/FURNISHINGS - CARGO COMPARTMENTS - INTRODUCTION Purpose The cargo compartments provide space to carry luggage and freight. Abbreviations and Acronyms

− fwd - forward − mid - middle − typ - typical − ref - reference



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EQUIPMENT/FURNISHINGS - CARGO COMPARTMENTS - FORWARD CARGO - ACCESS PANEL Purpose The access panel lets you enter the forward cargo compartment from the passenger compartment. Physical Description The panel is 20 inches long and 20 inches wide (508 mm by 508 mm). There is a handle on the top side of the panel. The panel is attached with quick-release fasteners. Location The panel is on the right side of the passenger compartment. It is below a floor panel (near the tenth window cutout from the front) that is covered by a section of carpet with a serge around the edges. Training Information Point You use the access panel when the forward cargo door is difficult to unlatch. This could be caused by blockage of the inner handle latch mechanism. If the aft cargo door is difficult to unlatch, use the aft ceiling blowout panel. This panel is on the right side of the passenger compartment floor. It is near the eight window cutout from the rear.

See the pressurization chapter for more information on the aft cargo compartment blowout panel. (SECTION 21-30)



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - INTRODUCTION General Description Emergency equipment typically includes these items:

− Overwing escape straps − Escape lanyards − Detachable emergency equipment − Escape slides.

Emergency equipment requirements depend on the airplane mission profile. The equipment put on the airplane matches the specific requirements of the mission. See your operations manual and applicable regulations to determine the minimum emergency equipment. Refer to the component operation instructions and placards for method of use. Location See your operations manual to determine the types, quantity, and locations of the emergency equipment. Placards on the airplane identify the locations of emergency equipment.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - OVERWING ESCAPE STRAPS Purpose Overwing escape straps permit passengers to move safely over the wing and to the ground. Physical Description The escape strap has these items:

− Strap − Hook − Anchor fitting − Stowage tube.

The escape strap is in a stowage tube in the ceiling of the passenger compartment. One end of the strap attaches to the doorway structure of the emergency exit door. You remove the emergency exit door to gain access to the strap. In an emergency, attach the hook end of the strap to a fitting on the wing. Location Overwing escape straps are in stowage tubes above each emergency exit door.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - ESCAPE LANYARDS Purpose Escape lanyards let the flight crew move safely to the ground through the number 2 windows. Location The rope and stowage bag are behind doors in the flight compartment lining above the number 2 windows. Physical Description The escape lanyards have these components:

− Fitting − Core − Links − Hand holds − Jacket.

The core is a kevlar cord rated at 1500 pounds. Foam links space hand holds at regular intervals. A jacket of weaved kevlar covers the entire length of the lanyard. One end of the escape lanyard attaches to the airplane structure. The other end is coiled and stored in a stowage bag. To get access to the escape lanyards, unlatch the compartment cover.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - EMERGENCY LOCATOR TRANSMITTERS Purpose Emergency locator transmitters help rescue crews find airplanes which land away from an airport. The transmitters send a radio signal to satellites, other airplanes, and air traffic control facilities. Rescue crews use information from these sources to find the airplane. Physical Description The emergency locator transmitter is a compact, buoyant, automatic unit. Emergency locator transmitters have these parts:

− Transmitter − Battery − Antenna − Lanyard.

The transmitter provides a homing signal for civil and military search aircraft by automatically transmitting a swept-tone-modulated signal simultaneously on both the civil and military international VHF aeronautical distress frequencies (121.5 and 243.0 MHz). The battery is a silver chloride/magnesium primary cell. In the preactivated state the electrolyte is dry and the battery is inert. The battery is activated when the electrolyte gets wet with water. Immersion in water (as a result of an aircraft ditching) automatically activates the battery.

The antenna pivots and folds along the length of the emergency locator transmitter for stowage. Water-soluble tape retains the antenna in the stowed position. Emergency locator transmitters have a lanyard assembly and a yoke cable. The lanyard assembly has 60 feet of braided nylon cord and attaches to a flexible stainless-steel yoke cable. The yoke cable attaches to the battery case and wraps around the battery case. The lanyard cord is bifilar-wound on a holder card and the yoke cable and holder card attach to the battery case with water-soluble tape. A lanyard guide and the stowed antenna hold the nylon cord approximately four feet from the free end of the lanyard. For method of use, refer to the component operation instructions and placards. Location Emergency locator transmitters may be in these general locations:

− life rafts − Overhead stowage bins − Center ceiling compartments − Other stowage locations throughout the airplane.

See your operations manual to determine the types, quantity, and locations of the emergency locator transmitters. Placards on the airplane identify the locations of emergency equipment.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - DETACHABLE, FLIGHT COMPARTMENT Physical Description Detachable emergency equipment is in the flight compartment and passenger compartment. Flight Compartment This is the detachable emergency equipment in the flight compartment:

− Crash axe − Smoke goggles − Firegloves (stowage provisions) − Life vests (stowage provisions) − Flashlights (some installations) − Protective breathing equipment (some installations).

There are stowage provisions for firegloves and life vests. The stanchion at the second observer station has space provisions for two flashlights and protective breathing equipment. Installation depends on the airline requirements.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - DETACHABLE, PASSENGER COMPARTMENT Passenger Compartment This is the detachable emergency equipment in the passenger compartment:

− First aid kits − Megaphones − Life vests (stowage provisions) − Flashlights (some installations).

The quantity and types of first aid kits on the airplane depend on the airline requirements. See your operations manual to determine the quantity and locations of the first aid kits. There are two power megaphones in the passenger compartment. Stowage provisions are provided for life vests. Provisions are provided for installation of four flashlights with holders in the passenger compartment. Installation depends on the airline requirements. Additional detachable emergency equipment may be in the passenger compartment of the airplane. Emergency equipment requirements depend on the airplane mission profile. The equipment put on the airplane matches the specific requirements of the mission. See your operations

manual and applicable regulations to determine the minimum emergency equipment. See the component operation instructions and placards for method of use. Location See your operations manual to determine the types, quantity, and locations of the emergency equipment. Placards on the airplane identify the locations of emergency equipment.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - ESCAPE SLIDES Purpose Escape slides help passengers and crew evacuate the airplane in an emergency. If the airplane lands in water, you may disconnect the escape slides from the airplane and use them as flotation devices. Physical Description Escape slides are made of neoprene-coated nylon fabric. An aluminum coating provides protection from the effects of radiant heat. The sliding surface is a high strength, urethane-coated, nylon fabric. Each escape slide packs in a valise and stows inside a compartment on the aircraft exit door. A lighting system provides illumination of the ground during a night evacuation. Batteries operate the lighting system. The lighting system is a series of incandescent lamps on the end of the escape slide body. Escape slides have quick-release detachable girts. This feature allows the escape slides to separate easily from the aircraft so you may use them as flotation devices in the event of a ditching. It also provides for simple girt replacement. Each escape slide installation has these parts:

− Escape slide compartment − Escape slide pack − Two floor brackets.

The escape slide compartment holds the slide pack in the stowed position and opens when you use the slide. The escape slide pack is inside the escape slide compartment. The entire assembly attaches to the lower inboard face of each entry and service door. The floor brackets are at the forward and aft ends of the doorways, inboard of the door sill. Each slide has these additional features:

− Lifelines − Mooring line with a frangible link − Red handgrips.

Location An escape slide is on the lower inboard face of each entry and service door.



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EQUIPMENT/FURNISHINGS - EMERGENCY EQUIPMENT - ESCAPE SLIDES Training Information Point You arm and disarm the escape slide manually. When the escape slide is armed, the grit bar is secure in the escape slide floor brackets. When the escape slide is stowed (not armed), the girt bar is in the girt bar retainer hooks. Make sure the slide is not armed before you open the door. If you open the door when the slide is armed, the slide will deploy. Put the slide warning pennant across the door window when the slide is armed. The slide warning pennant will warn people outside the airplane that the door is armed.



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EFFECTIVITY YB202


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