Developed for Training Purposes Only
Maintenance Training Manual
Vol 07
EMBRAER ERJ-190 / 195 (GE CF34)
ATA 38 - WATER AND WASTE SYSTEM
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
FRONT MATTER
This manual is issued by Embraer Customer Training and SHALL BE USED
FOR TRAINING PURPOSES ONLY. The data contained herein, although its
update to the revision date, does not replace or supersede the information
contained in the Embraer ERJ-170/190 (GE CF34) airframe or engine
maintenance manuals or other official publications.
This Maintenance Training Manual (MTM) contains all necessary information
to fulfill the needs as a printed/electronic publication to support the theoretical
training activities in aircraft maintenance training. Where possible, duplication
of information has been avoided, however, certain data may be repeated
where it has been necessary to include such data to preserve the continuity
of subject matter.
This edition of the Maintenance Training Manual is based on the last version
of Embraer Technical Publications. No further revisions will be added to this
current issue, if printed.
MANUAL STRUCTURE
All manual contents are organized as follows:
TITLE PAGE
A title page with its identification as "Training Manual" and copyright
information.
FRONT MATTER BLOCK
The purpose of the front matter block is to explain the way this manual is
organized, and to inform which publications were used as source of
information.
TABLE OF CONTENT
The table of content shows a list of relevant items/pages contained in the
actual volume in an “Index” format.
CHAPTER DESCRIPTION BLOCK
The chapter description block has the technical information derived from the
Embraer Technical Publications and follows the modularity concept, thus its
contents may vary according to the course purpose (rating and the applicable
training level).
It is organized in a didactic manner to facilitate the learning process with
rearranged sequence of the applicable sub-chapters.
The body of each ATA chapter has a Title Page.
For additional information concerning this manual, contact EMBRAER
CUSTOMER TRAINING.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
Developed for Training Purposes Only
DISCLAIMER
The data and any other information contained herein (“Embraer Data”) are
only and exclusive property of Embraer S.A. and they cannot be disclosed
without the previous consent of Embraer S.A. The use of the Embraer Data is
exclusive for the specific purpose of training which is merely informative and
any other use of Embraer Data is expressly forbidden. Embraer does not
represent or endorse the accuracy or reliability of any advice, opinion,
statement, recommendation, guidance or any other information displayed or
established herein. Nothing contained in this authorization shall be deemed
to diminish or eliminate any right or remedy Embraer S.A may have at law or
in equity.
ATA 38 – WATER AND WASTE SYSTEM GENERAL (38-00).....................5
INTRODUCTION................................................................................. 6
GENERAL DESCRIPTION.................................................................6
COMPONENTS................................................................................ 12
OPERATION.....................................................................................24
POTABLE WATER (38-10).......................................................................28
INTRODUCTION............................................................................... 28
GENERAL DESCRIPTION...............................................................32
COMPONENTS................................................................................ 34
OPERATION.....................................................................................38
STORAGE AND DISTRIBUTION (38-11).................................................42
INTRODUCTION............................................................................... 42
GENERAL DESCRIPTION...............................................................42
COMPONENTS................................................................................ 44
OPERATION.....................................................................................58
WATER HEATER SYSTEM (38-12).........................................................62
INTRODUCTION............................................................................... 62
GENERAL DESCRIPTION...............................................................62
COMPONENTS................................................................................ 62
OPERATION.....................................................................................64
WATER TANK QUANTITY INDICATION (38-13)....................................66
INTRODUCTION............................................................................... 66
GENERAL DESCRIPTION...............................................................66
COMPONENTS................................................................................ 66
OPERATION.....................................................................................70
WASTE DISPOSAL (38-30)......................................................................74
INTRODUCTION............................................................................... 74
GENERAL DESCRIPTION...............................................................74
COMPONENTS................................................................................ 74
OPERATION.....................................................................................80
GRAY WATER - DRAIN SYSTEM (38-31)...............................................82
INTRODUCTION............................................................................... 82
GENERAL DESCRIPTION...............................................................82
COMPONENTS................................................................................ 86
OPERATION.....................................................................................90
VACUUM WASTE SYSTEM (VWS) (38-32)............................................92
INTRODUCTION......................................................................................92
GENERAL DESCRIPTION.......................................................................94
COMPONENTS....................................................................................96
OPERATION.........................................................................................110
AIR SUPPLY (38-40)..............................................................................114
INTRODUCTION 38-40-00.....................................................................114
GENERAL DESCRIPTION.....................................................................114
COMPONENTS....................................................................................116
OPERATION.........................................................................................120
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
TABLE OF CONTENTS
3
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Developed for Training Purposes Only
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
Developed for Training Purposes Only
ATA 38 - WATER AND WASTE SYSTEM
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
5
WATER AND WASTE SYSTEM GENERAL (38-00)
INTRODUCTION
The Water/Waste system provides waste collection and storage from the
toilet assemblies located within the lavatories and supplies pressurized
potable water in the galleys and in the lavatory areas for passenger and crew
use. The system is made up of potable water, waste disposal and air supply.
The waste disposal system is composed of two subsystems, the vacuum
waste system and the gray water drain System.
WATER SYSTEM
The Potable Water System supplies pressurized potable water in the galleys
and lavatories for passenger and crew use. The pressurization of the potable
water system is achieved by bleed air or an optional air compressor. The
potable water is stored in a central holding tank, whose useable capacity is
110 liters.
The water lines are installed inside the pressurized, temperature-controlled
environment of the fuselage. The water line to each consumer is equipped
with a manual shutoff valve for system isolation and maintenance actions.
The titanium waste lines for transporting the waste are installed inside the
pressurized, temperature-controlled environment of the fuselage and are
routed from the toilets to the waste holding tank.
During a toilet flush cycle, the Vacuum Waste System uses a small amount of
pressurized water from the potable water system to rinse the toilet bowl and
aid in the evacuation of waste.
During ground servicing, the waste tank is drained through a service panel
into a service truck. A rinse line routed from the service panel to a rotating
rinse nozzle within the waste tank is used to supply rinsing fluid to the tank.
The system controller operates and monitors the system components and
evaluates failure status.
Insulation and electric heaters are installed for the potable and gray water
systems in order to prevent freezing during normal flight and ground
operation.
The Gray Water System enables draining of the serviced water from galleys
and lavatories washbasins. Draining is performed by drain masts located in
the forward and aft sections of the fuselage..
The optional gray water intermediate holding tanks collect gray water on
ground from the forward and aft galleys and lavatories to avoid spillage onto
the tarmac.
A system controller (WWSC- Water and Waste System Controlller_operates
and monitors the system components, evaluates failure status and also
controls the water/waste heating systems.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
GENERAL DESCRIPTION
WASTE SYSTEM
The Vacuum Waste System provides waste collection and storage from the
toilet assemblies located within the lavatories for passenger use. It uses
either a vacuum generator or differential pressure between the cabin and
ambient to transport the waste from the toilets to an aft mounted waste
holding tank, whose usable capacity is 95 liters (25 gallons).
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Developed for Training Purposes Only
WATER/WASTE - OVERVIEW ACFT WITH AFT POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
7
WATER AND WASTE SYSTEM GENERAL (38-00)
GENERAL DESCRIPTION
WATER SYSTEM
The Potable Water System supplies pressurized potable water in the galleys
and lavatories for passenger and crew use. The pressurization of the potable
water system is achieved by bleed air; alternately, a standard air compressor
is used to pressurize the water system if the bleed air pressure is below the
optimal range. The potable water is stored in a central holding tank, whose
useable capacity is 110 liters; located in the forward fuselage section of the
aircraft under the floor in front of the forward bulkhead of the forward cargo
compartment..
Developed for Training Purposes Only
Developed for Training Purposes Only
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The Gray Water System enables draining of the serviced water from galleys
and lavatories washbasins. Draining is performed by drain port installed in
the forward fuselage for drainage of gray water on-ground drain masts, aft
master drains and by a relocated forward drain mast.
A system controller (WWSC- Water and Waste System Controlller) and
VCU- Valves Control Unit) operate and monitor the system components,
evaluates failure status and also controls the water/waste heating systems.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
WATER/WASTE - OVERVIEW EMB 195 ACFT WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
9
GENERAL DESCRIPTION
•
POTABLE WATER (AMM SDS 38-10-00/1)
•
WASTE DISPOSAL (AMM SDS 38-30-00/1)
•
AIR SUPPLY (AMM SDS 38-40-00/1)
•
WWSC (Water and Waste System Controller) (AMM MPP 38-00-01/401)
•
SUMP ASSEMBLY (AMM MPP 38-00-03/401)
Developed for Training Purposes Only
Developed for Training Purposes Only
The WATER/WASTE includes these subsystems:
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
•
VCU (Valve Control Unit) (AMM MPP 38-00-02/401)
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND
WWSC
The WWSC monitors and controls the components of the systems of the
potable water, vacuum waste, gray water and air supply. The controller
interacts with the aircraft aft FAP and with power systems.
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The WWSC and VCU monitor and control the components of the systems of
the potable water, vacuum waste, gray water and air supply. The controllers
interacts with the aircraft aft FAP (Flight Attendant Panel) and power
systems.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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WATER/WASTE - BLOCK DIAGRAM
EFFECTIVITY ACFT WITH AFT POTABLE WATER TANK
EFFECTIVITY:ON ACFT BEM 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
11
COMPONENTS
WASTE DISPOSAL (38-30)
The waste disposal system provides waste collection and storage from the
toilet assemblies located within the lavatories and from the gray water
coming from the galley sinks and lavatory washbasins. The waste disposal
system is composed of two subsystems, the VWS (Vacuum Waste System)
and the gray water drain system. The VWS uses either a vacuum generator
or differential pressure between the cabin and the ambient to transport the
waste from the toilets to a vacuum waste system tank.
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER (38-10)
The potable water subsystem includes components and equipment to store
and supply pressurized potable water to the galley and lavatory areas for the
use of passengers and crew members. The system supplies pressurized
water to the lavatories and the galleys. This water cannot be used to drink.
Water is also supplied in the lavatories for flushing of the vacuum toilets. The
potable water system is made up of other three systems: storage and
distribution, water heater, and water tank quantity indication.
AIR SUPPLY (38-40)
The potable water system is pressurized by bleed air coming from the APU
(Auxiliary Power Unit) or main engines or air compressor if applicable. The
air is introduced via an air manifold into the potable water tank to provide
regulated pressurized potable water.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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WATER/WASTE - MAIN COMPONENTS ACFT WITH AFT POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
13
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14
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WATER/WASTE - MAIN COMPONENTS ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
15
WATER WASTE SYSTEM CONTROLLER
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK
AND WWSC
The WWSC controls and performs the following functions:
The system FILL/DRAIN process is controlled jointly by the VCU and the
WWSC.
TRAINING INFORMATION POINTS
WWSC provides twelve (12) discrete pin-programming inputs to accept
aircraft configuration data. The pin programming inputs are hard-wired on the
aircraft side harness.
PIN PROGRAMMING OPTIONS
Developed for Training Purposes Only
Developed for Training Purposes Only
•
The WWSC is a microprocessor-based electronic module that monitors and
controls the components of the water, waste and air supply systems.
The WWSC is mounted in the rear electronics bay on a support bracket. The
location is behind the aft LH (Left- Hand) lavatory and above the vacuum
waste tank.
The controller operates with the aircraft 28 VDC (Volt Direct Current) power.
The WWSC is powered from one of three separate sources. The WWSC also
provides water tank fill and drain functions under a low-power condition called
Hot Bus mode.
The system controller operates and monitors the system components and
evaluates failure status.
The WWSC controls and performs the following functions:
•
•
•
•
•
•
•
•
•
•
•
•
•
System fill/drain process.
Water tank level monitoring.
Valve opening/closing.
Drain masts heating.
Waste tank level monitoring.
Initiation of vacuum generator operation at low altitudes.
Monitoring of service panel door switch.
Interface with toilet.
BIT (Built-in Test) of water system components;
Indication of water system status to cockpit, FAP and service panel;
Communication with the Generic I/O 3 (MAU 3) for fault messages
displayed in the CMC (Central Maintenance Computer).
In-flight drainage of the potable water (If applicable to the aircraft
configuration).
Gray water drainage (Gray water holding tank if applicable to the aircraft
configuration).
WATER WASTE SYSTEM CONTROLLER
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The WWSC is a microprocessor-based electronic module that interfaces with
the VCU, monitors and controls the components of the water, waste and air
supply systems.
.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
WATER/WASTE - MAIN COMPONENTS
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
17
VALVE CONTROL UNIT
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Developed for Training Purposes Only
Developed for Training Purposes Only
The VCU is a PLD - Programmable Logic Device that interfaces with WWSC,
controls and monitors the valves, air compressor, and Fill/Drain switch. The
VCU is installed in the aft avionics compartment and operates with the
aircraft 28 VDC power. The VCU is powered from one of three separate
sources: the aircraft DC GND SVC BUS, DC BUS 1 and HOT BUS (battery).
Generally, the DC GND SVC BUS will power the VCU, in case of loss of DC
GND SVC BUS, the DC BUS 1 provides power to VCU. The VCU
automatically switches to HOT BUS mode when both DC GND SVC BUS
and DC BUS 1 fail to supply power.
PIN PROGRAMMING
The VCU has only two optional pins. One indicates whether or not the aircraft
is an ERJ 190-200, because the VCU may be extended for use on other
aircraft models of the ERJ 170/190 aircraft in case of the fwd drain mast
relocation.
The other pin enables or disables a 180s time delay for gray water ground
valve closing after the aircraft takes off. The aim of this delay is to assure
clearing of the drain lines after the opening of the gray water valve (when
installed) and prior the closing of the gray water ground valve.
TRAINING INFORMATION POINTS
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The VCU fault indication system is monitored on FAP through the water fault
indication light (blinking) and also can be checked on the lighted indication
panel of the VCU.
The VCU indication panel has: the reset button; the LED (Light-Emitting
Diode) test button performs BIT of the gray water ground valve, FILL/ DRAIN
valve, FILL/DRAIN switch and overflow valve; the LED SYS FAIL indicates
VCU fault.
The VCU controls and performs the following functions:
•
•
•
•
•
•
The System fill process*
System drain process*
Overflow valve opening/closing.
On-ground draining of the potable water and gray water.
Air compressor operation.
Provisions for Communication with the MAU for fault messages displayed
in the CMC.
* The system FILL/DRAIN process is controlled jointly by the VCU and the
WWSC.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
18
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WATER/WASTE - MAIN COMPONENTS (ONLY FOR EMB 195) - VCU INDICATION LIGHTS
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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20
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WATER/WASTE - VCU INDICATION LIGHTS
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21
SUMP ASSEMBLY
For potable water, the fitting is a clamshell type and the ends are .50". For
gray water line, the fitting is beaded for a hose clamp and the ends are .75"
below floor and 1.00" above floor). The sump also contains a
condensate/excess water drain tube bonded to the sump basin. The tube is a
1/4" stainless tube, which is connected to a section of Tygon (PVC) tubing to
direct the water toward the aircraft bilge.
Developed for Training Purposes Only
Developed for Training Purposes Only
Sump assemblies are installed in the aircraft floor panels at the galley and
lavatory water system interface locations. The sump provides the connection
point for the potable water and gray water lines from the individual users. The
sump contains interface fittings for connection of the galley or lavatory water
hoses above floor and the water system hoses below floor.
The sump drain hose is used to drain water that may leak from the
connection points of the potable water and/or gray water lines.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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WATER/WASTE - MAIN COMPONENTS
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23
AIRCRAFT WITH AFT POTABLE WATER TANK – OPERATION
WATER SYSTEM OPERATION
The water system supplies pressurized water to lavatories and galleys
whenever the following conditions are met:
Electrical power is available
Water tank is not empty;
Fill/Drain Switch is in “NORMAL” position;
No cabin drain is requested in flight.
The WWSC is in normal mode of operation while powered by DC GND SVC
BUS or DC BUS 1. The WWSC automatically switches to HOT BUS power
when both DC GND SVC BUS and DC BUS 1 fail to supply power. In the
HOT BUS mode, all WWSC operates partially to allow for draining and filling
of the water tank when neither one of the above mentioned buses are
powered.
POTABLE WATER FILLING
The service panel door switch enables HOT BUS power to the WWSC when
the service panel door is open. If power from the DC GND SVC BUS and DC
BUS 1 is not available or fails to supply power, the WWSC automatically
switches to HOT BUS power mode so as to allow system filling and drainage.
Filling is started by selecting FILL position in the service panel door on
ground. The WWSC command the fill/drain valve to open and enable water to
be filled into the water tank via the fill/drain nipple at the service panel. The
opened valve also enables tank ventilation and overflow via the aft drain
mast. The WWSC stop filling If the water tank becomes full, by closing the
fill/drain valve and the provide FULL indication at the service panel and
quantity indication on the FAP (Flight Attendant Panel).
WASTE SYSTEM OPERATION
Toilet flushing is initiated by a passenger pushing the momentary contact
type flush switch located inside the lavatory. The WWSC connects to each
toilet flush control unit (FCU), mounted on the toilets, times and sequences
the operation of the vacuum toilet, by controlling the rinse valve and the toilet
flush valve. The WWSC provides power to the MSR according to altitude in
order to supply electrical power to the vacuum generator. The WWSC
receives flight and altitude information from the aircraft through MAU 3 via
ARINC 429 bus (Aeronautical Radio Incorporated).
If the waste tank becomes full, a level sensor in the waste tank notifies the
WWSC, which in turn disables the toilets to prevent further flushing, and
over-filling of the waste tank.
The WWSC monitors the aircraft service panel door switch contacts to
enable or disable toilet operation.
The WWSC monitors the Liquid Level Sensors (LLS) to enable or disable
toilet operation and provide indication on the Flight Attendant Panel (FAP).
The WWSC incorporates the necessary BIT to detect internal faults and
external faults, by performing BIT tests of the components and circuits.
The WWSC communicates with CMC via ARINC 429 bus through the MAU 3
for maintenance failure messages.
POTABLE WATER DRAINING
Draining is started by opening the service panel door on ground and turning
the fill/drain switch to the DRAIN position. The WWSC command the forward
drain valve and the fill/drain valve to open and enable water in the tank and
tubing to be drained via the forward and aft drain masts and the fill/drain
nipple. When the optional in-flight, aft drain valve is installed, the opening of
valve is delayed until the water level in the water tank falls below 10%. This
is done to allow proper venting and draining of the water tank. The fill/drain
switch also enables the forward drain valve to open during cold weather
conditions by overriding the safety thermostat inside forward drain mast.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
24
Developed for Training Purposes Only
Developed for Training Purposes Only
•
•
•
•
IN-FLIGHT WATER DRAINING
Both drain masts are temperature controlled by the WWSC. The drain mast
heaters prevent hazardous ice formation during draining of water. In case of
any faulty drain mast(s) condition., In-flight draining is not allowed by WWSC.
The WWSC opens and leaves open the following valves 2 minutes after it
detects that the landing gear is up. The valves are always closed while
landing gear is down except during the drain process.
Developed for Training Purposes Only
Developed for Training Purposes Only
WATER/WASTE - OPERATION
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
25
ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Due to the change of the water tank for the EMB 195, it was necessary to add
a new controller (VCU), two valves, and change the operation logic of the air
compressor. The VCU interfaces with the two added valves, WWSC
controller, air compressor, Fill/Drain switch, aft Flight Attendant Panel, and
have provisions for interfacing with the Centralized Maintenance Computer
(CMC). Some signals coming from the service panel switch, landing gear and
WWSC are also necessary for the VCU to operate jointly with the WWSC to
control the functionality of the system. The VCU does not interact or interface
with the waste system.
Developed for Training Purposes Only
Developed for Training Purposes Only
The Potable Water, Gray Water and Air Supply Systems are controlled and
monitored by the WWSC and VCU. The WWSC controls the Vacuum Waste
System. The WWSC and VCU interacts with the aircraft aft FAP, MAU 3 and
LICC, AICC and SPDA 1.
* The system FILL/DRAIN process is controlled jointly by the VCU and the
WWSC.
The WWSC communicates with CMC and also receives flight and altitude
information from the aircraft through MAU 3 via ARINC (Aeronautical Radio
Incorporated) 429 bus. The WWSC and VCU are in normal mode of
operation while powered by DC GND SVC BUS or DC BUS 1. The WWSC
and VCU automatically switch to HOT BUS power when both DC GND SVC
BUS and DC BUS 1 fail to supply power. In the HOT BUS mode, both
WWSC and VCU operate partially to allow for draining and filling of the water
tank when neither one of the above mentioned buses are powered.
For ground servicing, the WWSC and VCU incorporate a HOT BUS mode
feature that allows system servicing when electrical power is removed from
the aircraft generators or a GPU. The drainage of the system in HOT BUS
mode is done by gravity through the drain port and only the residual water
from the lines installed aft the wing box is drained through the service panel
and aft drain mast.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
26
Developed for Training Purposes Only
Developed for Training Purposes Only
WATER/WASTE – OPERATION ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
27
POTABLE WATER (38-10) - INTRODUCTION
The bleed air pressure is used as the primary pressure source of the system.
The bleed pressurization line is routed from the main aircraft bleed air duct up
to the water tank inlet distribution air manifold. The tap off point is placed in
such way to provide bleed air either from the engines or from APU. The bleed
air is filtered and regulated to the system operating pressure of 36 to 41 psig.
Alternately, an air compressor if applicable can be used to pressurize the
water system if the bleed air pressure is below the optimal range. The
pressure switch mounted to the water tank signals the WWCS, which
activates the air compressor to achieve the required water system pressure.
The potable water storage tank maximum useable capacity is pinprogrammable.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
Developed for Training Purposes Only
Developed for Training Purposes Only
The potable water subsystem includes components and equipment to store
and supply pressurized potable water to the galley and lavatory areas for the
use of passengers and crew members. The system supplies pressurized
water to the lavatories and the galleys. This water cannot be used to drink.
Water is also supplied in the lavatories for flushing of the vacuum toilets. The
potable water system is made up of other three systems: storage and
distribution, water heater, and water tank quantity indication.
28
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Developed for Training Purposes Only
POTABLE WATER – OVERVIEW AIRCRAFT WITH AFT POTABLE WATER TANK AND WWSC
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
29
INTRODUCTION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The bleed air pressure is used as the primary pressure source of the system.
The bleed pressurization line is routed from the main aircraft bleed air duct up
to the water tank inlet distribution air manifold. The tap off point is placed in
such way to provide bleed air either from the engines or from APU. The bleed
air is filtered and regulated to the system operating pressure of 36 to 41 psig.
Alternately, an air compressor is used to pressurize the water system if the
bleed air pressure is below the optimal range. The pressure switch mounted
to the water tank signals the VCU, which activates the air compressor to
achieve the required water system pressure. The air compressor is also
used during drainage of the system through the service panel.
The potable water storage tank maximum useable capacity is pinprogrammable in the same way for the EMB 195.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
Developed for Training Purposes Only
Developed for Training Purposes Only
The potable water subsystem includes components and equipment to store
and supply pressurized potable water to the galley and lavatory areas for the
use of passengers and crew members. The system supplies pressurized
water to the lavatories and the galleys. This water cannot be used to drink.
Water is also supplied in the lavatories for flushing of the vacuum toilets. The
potable water system is made up of other three systems: storage and
distribution, water heater, and water tank quantity indication.
30
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER – OVERVIEW ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
31
GENERAL DESCRIPTION
The POTABLE WATER includes these subsystems:
•
•
•
Storage And Distribution (AMM SDS 38-11-00/1)
Water Heater System (AMM SDS 38-12-00/1)
Water Tank Quantity Indication (AMM SDS 38-13-00/1)
ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Operation and monitoring is made by two system controllers, WWSC (Water
and Waste System Controller) and VCU (Valve Control Unit), which control
the potable water system components. These systems have failure detection
capability and display messages indicating the current system status on the
FAP, on the CMC, and also in the VCU LED (Light-Emitting Diodes).
The supply line in the galley contains a water filter if applicable for removing
impurities and sediment, and improving the water taste and quality for the
use of passengers and crew members.
Developed for Training Purposes Only
Developed for Training Purposes Only
The potable water hoses extend from the water tank to the consumers;
galleys and lavatories.
A self-regulating water heater if applicable is installed at the lavatories to
provide warm water for hand washing with the aim of improving the
passenger's comfort as well as allowing the crew members to clean their
hands.
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK
The system is pressurized through the air manifold by means of bleed air
coming from the APU (Auxiliary Power Unit) or from the main engines or
even from the air compressor if applicable (AMM SDS 38-40-00/1).
Operation and monitoring is made by one system controller, WWSC (Water
and Waste System Controller), which controls the potable water system
components. WWSC has a failure detection capability and displays
messages indicating the current system status on the FAP (Flight Attendant
Panel) and on the CMC (Central Maintenance Computer). Water quantity is
permanently monitored by the level sensor. The water tank quantity
indication, at the FAP, shows the following percentage figures: 0%; 25%;
50%; 75%, 100%. The potable water is filled /drained through the service
panel. The service panel indication gives the current status of the potable
water system: FULL, when the system is filled (to set the fill/drain switch to
FILL); DRAIN, when the drain function is activated (to set the fill/drain switch
to DRAIN). When the fill/drain switch is set to NORMAL, the indication in the
service panel disappears. The water lines are equipped with a manual shutoff
valve for galley and lavatory system isolation and for maintenance without the
use of tools.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
32
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER - BLOCK DIAGRAM ACFT WITH AFT POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
33
COMPONENTS
STORAGE AND DISTRIBUTION (38-11)
Potable water is distributed from a single tap point below the potable water
tank through the water distribution line. The water lines distribute the potable
water to the lavatories and the galleys for the use of passengers and crew
members.
Developed for Training Purposes Only
Developed for Training Purposes Only
WATER HEATER SYSTEM (38-12)
A self-regulating water heater if applicable is installed in the lavatories to
provide warm water for hand washing, aimed at improving passenger comfort
as well as allowing the crew members to clean their hands, prior to beginning
the food servicing duties.
WATER TANK QUANTITY INDICATION (38-13)
The water tank quantity indication subsystem includes components to
indicate and monitor the water level within the potable water tank. The
system is made up of water tank level sensor and service panel indication.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
34
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER - MAIN COMPONENTS ACFT WITH AFT POTABLE WATER TANK
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
35
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Developed for Training Purposes Only
THIS PAGE INTENTIONALLY LEFT BLANK
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36
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER - MAIN COMPONENTS ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
37
OPERATION
For ground servicing, the WWSC incorporates a HOT BUS mode feature that
allows system filling and draining even without electrical power being
supplied by either the AC (Alternating Current) generators or by the GPU
(Ground Power Unit). The service panel door switch enables HOT BUS
power to the WWSC when the service panel door is open. If power from the
DC (Direct Current) GND (Ground) SVC (Service) BUS and DC BUS 1 is not
available or is not supplied, the WWSC automatically switches to HOT BUS
power mode, so as to allow the system filling and drainage.
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND
WWSC
FILLING
The filling of the potable water tank system starts by opening the service
panel door on ground, attaching a fill hose, and turning the fill/drain switch to
the FILL position. The fill/drain valve turned to the OPEN position, enabling
water to be filled into the water tank through the fill/drain nipple at the service
panel.
If the water tank becomes full, the fill/drain valve closes automatically and the
FULL indicator is illuminated at the service panel. When the fill/drain switch
returns to NORMAL, the fill/drain valve closes simultaneously and the FULL
indication dims. The valves are also closed if the 6-minute time-out expires in
the HOT BUS power mode.
A 10-second time-out period is incorporated to shut down the WWSC and
avoid battery depletion. The service panel door switch disconnects the
WWSC from the HOT BUS every time the service panel door is closed. The
WWSC activates the air compressor if applicable when the water tank
pressure switch indicates low pressure, except when the FILL signal is active
while the aircraft is parked on the ground.
DRAINING ON GROUND
On the ground, draining starts by opening the service panel door and turning
the fill/drain switch to the DRAIN position. The FWD (Forward) drain valve
and the fill/drain valve open automatically and enable water in the tank and
lines to be drained through the service panel in the aft section of the aircraft.
At the service panel, the DRAIN indicator light illuminates, indicating that all
valves are open. If the fill/drain switch is returned to NORMAL, all valves
close and the DRAIN indication dims.
At water consuming locations, the shutoff valves must be open. The faucets
and coffee makers are self-venting to clear the lines and avoid vacuum lock.
The drain servicing procedure using the compressor is not available by
means of hot battery power. In this mode, all valves open and the potable
water is drained on the ground by gravity through the drain mast and the
fill/drain nipple. The compressor is also commanded ON by the WWSC
during the pressurized drainage. The service panel door switch disconnects
the WWSC from the HOT BUS after 6 minutes when the fill/drain switch is set
to the DRAIN position.
DRAINING IN FLIGHT (IF APPLICABLE TO THE AIRCRAFT
CONFIGURATION)
In-flight drainage of the potable water tank is commanded by pressing the
water dump pushbutton indicator located in the cockpit (main instrument
panel). It is used by the flight crew for in-flight drainage of the potable water
tank. When the pushbutton is pressed, the aft drain valve opens automatically
and the cockpit water drain WHITE indicator is illuminated by the WWSC.
The water in the potable water tank is drained via the aft drain mast. When
the cockpit indicator is ON, the drainage can STOP if the cabin drain
pushbutton is pressed a second time, all water drain valves will close and the
WHITE indicator will extinguish. The forward drain valve is opened
automatically three minutes after water quantity inside the water tank
measures as 0%. The in-flight drainage inhibit via WWSC in case the landing
gear is down or the temperature sensor in the forward drain mast detects low
temperature. The forward and the aft drain valves are commanded to close.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
38
Developed for Training Purposes Only
Developed for Training Purposes Only
Potable water is distributed from a single tap point below the potable water
tank through the water distribution line. The water lines distribute the potable
water to the lavatories and galleys. Water is filtered in the galleys and is
warmed in the lavatories for the use of passengers and crew members. The
filling is done from service panel to the potable water tank. The on-ground
draining can be done through the service panel and the in-flight if applicable
through the drain masts.
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER – OPERATION ACFT WITH AFT POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
39
OPERATION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
For ground servicing, the WWSC and VCU incorporate a HOT BUS mode
feature that allows system filling and draining even with no electrical power
from either the AC generators or GPU. The service panel door switch
enables HOT BUS power to the WWSC and to the VCU when the service
panel door is open. If power from the DC GND SVC BUS and DC BUS 1 is
not available or fails to supply power, the WWSC and VCU automatically
switches to HOT BUS power mode so as to allow system filling and drainage.
FILLING
The filling of the potable water tank system starts by opening the service
panel door on the ground, attaching a fill hose, and turning the fill/drain switch
to the FILL position. The fill/drain valve (commanded by the WWSC) and the
overflow valve (commanded by the VCU) are automatically turned to the
OPEN position, which enables water to be filled into the water tank through
the fill/drain nipple at the service panel. If the water tank becomes full, the
fill/drain valve CLOSES automatically and the FULL indicator is illuminated at
the service panel. When the fill/ drain switch is returned to NORMAL, the
fill/drain valve closes simultaneously and the FULL indication dims. The
valves are also closed if a 6-minute time-out expires in the HOT BUS power
mode. After the valve closing command (10-second time-out period) expires,
the WWSC and VCU shutdown, avoiding battery depletion.
DRAINING ON GROUND
On-ground draining starts by opening the service panel door and turning the
fill/drain switch to the DRAIN position. When the fill/ drain switch is set to
DRAIN, the VCU commands the fill/drain valve and overflow valve to open.
The fill/drain valve opens automatically and enables water in the tank and
enables water in the tank and hoses to be drained through the service panel
in the aft section of the aircraft. If AC power is available the compressor
On the service panel, the DRAIN indicator starts blinking, indicating that the
initial drain process is in progress. Two minutes after the water tank is empty,
as detected by the water tank level sensor, or 17 minutes after the
compressor started working, the VCU will turn off the compressor and send a
signal to the WWSC to open the FWD DRAIN valve to allow drainage, by
gravity, of the remaining water in the system. On the service panel, the
DRAIN indication light illuminates steadily, indicating that all valves are open.
When the fill/drain switch is returned to NORMAL, all valves close and the
DRAIN indication dims on the service panel and the power to the air
compressor is enabled.
The drain servicing procedure using the compressor is not available by
means of hot battery power. In this mode, all valves open and the potable
water are on-ground drained by gravity through the drain port. Only the
residual water is drained through the aft drain mast and the fill/drain nipple. A
vent valve has been added to the top of the tank, allowing proper venting of
the tank and avoiding a build-up of vacuum during the gravity drainage since
the overflow hose will be filled up with water. The service panel door switch
disconnects the WWSC from the HOT BUS after 6 minutes, when the
fill/drain switch is set to the DRAIN position.
ABNORMAL OPERATION
FILLING
The open overflow valve enables the tank ventilation and overflow through
the forward drain port in case of water level sensor failure.
DRAINING IN FLIGHT (If applicable to the aircraft configuration)
In-flight draining is not allowed under any faulty drain mast condition and if
the landing gear information is not available. If the command is given after
the landing gear extension, the in-flight drainage will be inhibited and the
WHITE indicator will not illuminate.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
40
Developed for Training Purposes Only
Developed for Training Purposes Only
Potable water is distributed from a single tap point below the potable water
tank through the water distribution line. The water lines distribute the potable
water to the lavatories and the galleys. The water is filtered in the galleys and
the water is also warmed in the lavatories for the use of passengers and crew
members. The filling is done from the service panel to the potable water tank.
The on-ground draining can be done through the service panel, and in-flight if
applicable through the drain masts.
simultaneously turns on to pressurize the water through the water lines to the
service panel.
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Developed for Training Purposes Only
POTABLE WATER – OPERATION ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
41
STORAGE AND DISTRIBUTION (38-11)
•
•
•
•
•
•
•
•
•
•
•
Potable water tank
Water supply hoses
Fill/Drain valve
Forward drain valve
Fill/Drain nipple
Fill/Drain switch
Service panel door switch
Manual shutoff valves
Water filters
Lavatory faucets
Galley spigots
GENERAL DESCRIPTION
The potable water is filled through the single potable water service panel.
Potable water hoses extend from the water tank to the consumers: galleys
and lavatories. Potable water is distributed from the potable water tank
through the distribution lines. Reinforced and flexible supply hoses are
installed in the pressurized area under the floor cabin, except for the wing
area, where the water lines are routed above floor behind dado panels. The
water lines to each consumer are equipped with a manual shutoff valve for
system isolation and maintenance. Water is supplied to the sink by a wallmounted faucet located above the lavatory sink basin. Water is also supplied
to a spigot in the galleys.
Developed for Training Purposes Only
Developed for Training Purposes Only
INTRODUCTION
Potable water is distributed from a single tap point below the potable water
tank through the water distribution line. The water lines distribute the potable
water to the faucets of the lavatories and water spigots in the galleys for the
use of passengers and crew members.
The water storage and distribution system has the following equipment:
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK IN-FLIGHT
DRAINAGE
•
•
Cockpit in-flight drainage panel
Aft drain valve
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
• Overflow valve
• Water tank vent valve
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
42
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - BLOCK DIAGRAM
IF APPLICABLE TO THE AIRCRAFT CONFIGURATION.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
43
POTABLE WATER TANK
The potable water tank stores a varying quantity of water to be supplied to
lavatories and galleys on ground and during flight. The potable water storage
tank is located behind the aft cargo compartment bulkhead (below the cabin
floor crossbeams) in the aft section, and is mounted horizontally with two
band clamps. The tank is supported by a structural cradle that is attached to
the aircraft structure. At the top of the tank, a 4-inch V-Flange is installed.
The flange incorporates ports and fittings for the overflow line, air
pressurization, air pressure switch, and level sensor. At the bottom of the
tank, a flange connection provides an interface to the fill/drain and distribution
lines. An overflow tube set at 101% of tank level is provided to limit tank
volume in case of malfunctioning of the control loop, and as a protection
against overfilling. Water supply is provided by pressurization of the air
cushion above the water level.
Developed for Training Purposes Only
Developed for Training Purposes Only
COMPONENTS
The WWSC (Water and Waste System Controller) system controller, in
conjunction with the level sensor, limits the usable quantity to the predefined
volume.
NOTE: The aircraft potable water tank can be configured to 35, 70, 90 or
110-liters capacity by changing the WWSC pin programming.
The useable tank capacity is 110 liters. The tank has an air cushion volume
of 10 liters that provides proper dampening of tank pressure variations of the
bleed air pressure. An overflow tube set at 101% of tank level is provided to
limit tank volume in case of malfunctioning of the control loop, and as a
protection against overfilling.
The system controller, in conjunction with the level sensor, limits the usable
quantity to the pre-defined volume. Water supply is provided by
pressurization of the air cushion above the water level. The nominal system
pressure inside the tank is 36 - 41 psig considering an inlet pressure on
pressure regulator from 44 to 59.4 PSIG.
POTABLE WATER SUPPLY HOSES
Potable water flexible hoses are installed to supply potable water to the
consumers (lavatories and galleys). Clamshell couplings are used in the
connections of the hoses to the installed equipment. The hoses are clamped
to support brackets on the aircraft structure using saddle clamps with an
insulating sleeve. The supports are spaced enough to avoid the hose to
droop and thus ensure complete drainage.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
44
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS ON ACFT WITH AFT POTABLE WATER TANK
LENGTH
1072,6 mm (42,33 in)
DIAMETER
396,0 mm (15.60 in)
VOLUME, TOTAL
121,71 (32.1 USG)
VOLUME, USEABLE
110,01 (29.0 USG)
WEIGHT
16,0 kg (35.3 lb)
OPERATING TEMPERATURE
-54 def. C to +85 deg. C
(-65 deg. F to +185 def. F)
OPERATING PRESSURE
0 to 2862 hPa (0 to 41 PSIg)
MAX. OPERATING PRESSURE
3585 hPa (0 to 52 PSIg)
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
45
The potable water tank stores a varying quantity of water to be supplied to
lavatories and galleys on ground and during flight. The potable water storage
tank is located behind the forward cargo compartment bulkhead (below the
cabin floor crossbeams) in the forward section, and is mounted horizontally
with two band clamps. The tank is supported by a structural cradle that is
attached to the aircraft structure. At the top of the tank, a 4-inch V-flange is
installed. The flange on the top of the tank incorporates ports and fittings for
the overflow line, vent valve, air supply line, and level sensor. At the bottom
of the tank, a flange connection provides an interface to the fill/drain and
distribution lines. An overflow tube set at 101% of tank level is provided to
limit tank volume in case of malfunctioning of the control loop, and as a
protection against overfilling. Water supply is provided by pressurization of
the air cushion above the water level.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
Developed for Training Purposes Only
Developed for Training Purposes Only
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK POTABLE WATER TANK
46
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
47
COMPONENTS
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND
WWSC
Developed for Training Purposes Only
Developed for Training Purposes Only
FILL/DRAIN VALVE
The fill/drain valve enabling on-ground filling and draining as well as tank
ventilation and overflow via the aft drain mast, and draining during flight if
applicable. The valve is a four-way, two-position ball-type that is operated
by an electric motor, controlled by the WWSC. The nominal operating voltage
is 28 VDC (Volt Direct Current), supplied to the valve through the WWSC
from the DC GND SVC BUS or DC BUS 1. The fill/drain valve is designed to
withstand freezing conditions (AMM SDS 30-71-00/1).
FORWARD DRAIN VALVE
The FWD drain valve serves to on-ground drain the FWD potable water
system line and in-flight drain if applicable through the drain port. The valve is
operated by electrical signals from the WWSC. The FWD drain valve is a
two-way ball-type that is operated by an electric motor.
AFT DRAIN VALVE
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK IN
FLIGHT DRAINAGE
The AFT drain valve is used to in-flight drain the potable water tank. The
valve is a two-way, two-position ball-type that is operated by an electric
motor. The valve is operated by an electric motor controlled by the WWSC.
The nominal operating voltage is 28 VDC, supplied to the valve through the
WWSC from the DC GND SVC BUS or the DC BUS 1.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
48
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS ON ACFT WITH AFT POTABLE WATER TANK
IF APPLICABLE TO THE AIRCRAFT CONFIGURATION.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
49
COMPONENTS
(EFFECTIVITY: AIRCRAFT WITH FWD POTABLE WATER TANK)
Developed for Training Purposes Only
Developed for Training Purposes Only
FILL/DRAIN VALVE
The fill/drain valve is used for on-ground filling and draining the water system
and in-flight draining if applicable. The valve is a two-way; two position balltype that is operated by electrical signals from WWSC and VCU (Valve
Control Unit). The nominal operating voltage is 28 VDC, supplied to the valve
through the WWSC and VCU from the DC GND SVC BUS or DC BUS 1. The
fill/drain valve is designed to withstand freezing conditions (AMM SDS 30-7100/1).
FORWARD DRAIN VALVE
The FWD (Forward) drain valve serves to on-ground drain the FWD potable
water system line and in-flight drain if applicable through the drain port. The
FWD drain valve is a two-way ball-type that is operated by an electric motor.
The valve is operated by electrical signals from the WWSC. The FWD drain
valve is designed to withstand freezing conditions (AMM SDS 30-71-00/1).
OVERFLOW VALVE
The overflow valve installed close to the water tank in the FWD section for
ventilation and overflow purposes. The overflow valve opens for the filling
process when operating on ground, through the service panel and serves to
vent the tank in normal conditions and drain water on ground through the
drain port, in case the water level sensor is not operating. The normal
position for the valve in flight is CLOSED. The overflow valve is a two-way
ball-type that is operated by an electric motor controlled by the VCU. The
overflow valve is designed to withstand freezing conditions (AMM SDS 3071-00/1).
VENT VALVE
A vent valve is installed in the overflow line. This valve is installed to allow
proper venting of the water tank, during the gravity drainage when operating
on ground in the HOT BUS mode. Under this operating condition, the
overflow line is filled with water; therefore tank venting is not possible through
the corresponding hose.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
50
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
51
The service panel contains the necessary servicing equipment such as
fill/drain nipple, fill/drain switch, service panel door switch and a service
indication panel (AMM SDS 38-13-00/1). Identification placards in the English
language are provided to describe the equipment position/function. Bilingual
instructional placards with the description of all the service procedures steps
are provided (English and another language chosen by the airline).
FILL/DRAIN NIPPLE
The FILL/DRAIN nipple is part of the potable water service panel. It is the
connection between the potable water system and the potable water service
vehicle. It is used for filling and draining the potable water tank.
FILL DRAIN SWITCH
The fill/drain switch is part of the potable water service panel and enables
ground service operation of the system. The fill/drain switch activates the
following functions:
•
•
•
•
•
•
Potable water tank filling
Potable water tank draining
The FILL/DRAIN nipple is provided with these four main parts:
A standard adapter for the connection with the potable water vehicle.
A fitting for installation to the potable water hose.
A lever lock cap assembly.
An insulated base.
The fill/drain nipple has a cuff heater with an overheat protection and
temperature control. (AMM SDS 30-71-00/1).
The fill/drain switch is operated by electrical signals at 28 VDC. Three
positions that are actuated by the handle are possible and marked with
labels:
•
•
•
Drain
Normal
Fill
SERVICE PANEL DOOR SWITCH
The door switch is located in the potable water service panel. It is of
electromechanical type provided with a spring-loaded plunger. When the
service panel door is open, the door switch is used to connect the 28 VDC
electrical power from the aircraft HOT BATTERY BUS to the WWSC during
the system ground servicing, when no aircraft power or ground power is
available.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
52
Developed for Training Purposes Only
Developed for Training Purposes Only
SERVICE PANEL
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
53
POTABLE WATER FILLING
The service panel door switch enables HOT BUS power to the WWSC when
the service panel door is open. If power from the DC GND SVC BUS and DC
BUS 1 is not available or fails to supply power, the WWSC automatically
switches to HOT BUS power mode so as to allow system filling and drainage.
Filling is started by selecting FILL position in the service panel door on
ground. The WWSC command the fill/drain valve to open and enable water to
be filled into the water tank via the fill/drain nipple at the service panel. The
opened valve also enables tank ventilation and overflow via the aft drain
mast. The WWSC stop filling If the water tank becomes full, by closing the
fill/drain valve and the provide FULL indication at the service panel and
quantity indication on the FAP (Flight Attendant Panel).
POTABLE WATER DRAINING
Draining of the system will be performed simultaneously for the potable water
and optional gray water systems. The manual on-ground drain procedure is
described as follows:
The fill procedure is described as follows:
•
•
•
•
•
•
Open the water service panel, (LH side in the lower part of the fuselage);
Connect water supply hose from the service unit to the fill/drain nipple;
Set fill/drain switch to FILL position;
WARNING: DO NOT TOUCH THE DRAIN MAST. IF YOU TOUCH IT, YOU
WILL BE BURNED.
•
•
•
•
Open the water service panel, (LH side in the lower part of the fuselage;
Set fill/drain switch to DRAIN position;
Water drains through the drain masts and service panel fill/drain nipple;
The service panel light provides a DRAIN indication (all system valves
open) (except during HOT BUS operation mode);
Turn the fill/drain switch to the NORMAL position
All valves close and the Drain indication turns off.
Put the protective cap on the fill/drain nipple.
NOTE:
CAUTION: THE MAXIMUM PRESSURE FOR FILLING IS 379.3 kPa (55
Psi).
•
Let all unwanted water drain before you put the protective cap on the
fill/drain nipple.
•
•
•
Where there are freezing conditions, after the water drainage, we
recommend that you wait approximately 30 minutes to put the protection
cap on the fill/drain nipple to make sure that all residual water is drained.
This procedure will prevent the residual water freezing. The protection cap
can cause a blockage of the water/fill drain line.
•
•
•
•
Fill water system from Water Servicing unit;
The service panel light provides a FULL indication (except during HOT
BUS operation mode);
After FULL indicator illuminates the fill/drain valve closes automatically;
On the aft flight ATDT panel, make sure that the water quantity-indication
light shows the correct level.
Turn the fill/drain switch to the NORMAL position
Disconnect the water supply hose and close the service panel door.
NOTE: Let all unwanted water drain before you put the protective cap on
the fill/drain nipple.
Where there are freezing conditions, after the water drainage, we
recommend that you wait approximately 30 minutes to put the protection cap
on the fill/drain nipple to make sure that all residual water is drained. This
procedure will prevent the residual water freezing. The protection cap can
cause a blockage of the water/fill drain line.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
54
Developed for Training Purposes Only
Developed for Training Purposes Only
WATER SERVICING
Developed for Training Purposes Only
Developed for Training Purposes Only
WATER - SERVICING
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
55
MANUAL SHUTOFF VALVE
The water system may be isolated by means of the manual shutoff valve in
case of a water system leak in the supply line. The manual shutoff valve is
placed in the potable water supply line, at the galley and lavatory. The
equipment is installed above the floor level and is readily accessible.
GALLEY SPIGOT
The galley water spigot is mounted in the work counter area of the galley.
The water spigot is connected to the potable water system and supplies
water for passenger and crew use. The faucet is self-vented. The outlet has a
removable cap with an integral mesh screen to avoid contamination.
Developed for Training Purposes Only
Developed for Training Purposes Only
LAVATORY FAUCET
Water is supplied to the lavatories through a faucet located above the sink
basin with the faucet outlet. The faucet outlet is located a minimum of 1 inch
from the maximum rim level of the washbasins in order to prevent crosscontamination with the serviced water. The faucet incorporates a mechanical
time delay device to allow the continuous flow without holding down the cap.
The timer is adjustable from 3 to 10 seconds per push.
The faucet has a single control cap that serves to both initiate the flow of
water and control the water temperature (AMM SDS 38-12-00/1). The faucet
has two inlet ports for hot and cold water. A valve inside the body of the
faucet controls the flow and mixing from the two ports to regulate the water
temperature according to the set position. Red and blue arrows engraved on
the cap mark the hot and cold turn directions.
WATER FILTER
The potable water supply line in the galley contains a water filter for removing
impurities and improving the water taste and quality for use. The filters
remove unpleasant tastes and odors, organic pollutants, dirt, amoebic and
other cysts, algae and invisible particles, as small as two to five micrometers
in diameter. The filter reduces chlorine levels to fractional parts per million to
improve taste and prevents recontamination of the water from internal
bacteria growth. The filter element is an ultra fine disposable straining
material that must be replaced at periodic intervals.
NOTE: The filter is not designed to convert non-potable water into potable
water.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
56
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION - MAIN COMPONENTS
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
57
OPERATION
Filling and draining of the system is possible manually. The WWSC is able to
monitor failures of components connected and address failure message WTR
FILL DRAIN VLV/WWSC/WRG FAULT to the CMC and FAP. Only if the
Valve fails OPEN the FAP message will be displayed.
•
The WWSC provides control and power for opening and closing of all water
system valves. The position of the valve is monitored by the WWSC to
determine of there is a valve fault. The controller has protective circuitry to
prevent damage to the controller and electrical wiring in case of a short circuit
at the valve outputs. The circuit will automatically restore functioning after
the short is removed. At least one of the following methods are used to
provide short circuit protection: Fault Protected Drivers, Resettable fuses in
series with the output, Series resistance and Transient Suppression Devices.
Filll and drain indication is performed by LEDs marked “FULL” and “DRAIN”.
28 VDC Input power is supplied by the WWSC, which also controls the
indicator lights.
Developed for Training Purposes Only
•
•
FAP: WATER SERVICE/FAULT, 100% QUANTITY INDICATION, 75%
QUANTITY INDICATION, 50% QUANTITY INDICATION, 25%
QUANTITY INDICATION, 0% QUANTITY INDICATION.
Cockpit: CABIN DRAIN INDICATION.
Service Panel: TANK FULL, DRAIN VALVES OPEN.
The WWSC is able to monitor failures of components connected and address
failure messages to the CMC and FAP. Failure messages are addressed to
the FAP only if they affect flight attendant duties or passenger comfort. The
WATER SERVICE FAULT message is provided to the FAP under the
following conditions: Fill/Drain valve fails to CLOSE, FWD Drain valve fails to
CLOSE, Aft Drain valve fails CLOSE, FWD or AFT Gray Water Drain valve
fails to OPEN, Indicated temperature of the forward drain mast is
continuously less than 15C (59F) for 5 minutes. Indicated temperature of
either drain mast is continuously greater than 120C (248F) for 2 minutes.
The WWSC monitors the water tank level by means of the water tank level
sensor to determine the tank content quantity and sends an output signal to
the FAP to indicate the correct quantity. The level sensor measures the water
level within the potable water tank. The potable water tank level sensor is
continuously monitored, and the quantity is indicated at the FAP.
The service panel door switch enables HOT BUS power to the WWSC when
the service panel door is open. If power from the DC GND SVC BUS and DC
BUS 1 is not available or fails to supply power, the WWSC automatically
switches to HOT BUS power mode so as to allow system filling and drainage.
During servicing a minimum of electrical power for valve and the tank level
sensor operation is consumed by the WWSC. When the fill/drain switch is
returned to the NORMAL position, all valves automatically close. A 10second timeout period is incorporated to shut down the WWSC and avoid
battery depletion. The service panel door switch disconnects the WWSC from
the HOT BUS every time the service panel door is closed.
The WWSC detects a faulty Fill/Drain Valve if the requested position
(OPEN/CLOSED) is not in accordance (after 5 sec.) with the indicated
position (by the valve internal position switches). If the valve fails in open
position, the potable water system is not available. If the valve fails in closed
position, the potable water system is only available as long as water is in the
tank.
FILLING
Filling is s fill/drain switch to the FILL position. If the water tank becomes full,
the fill/drain valve closes automatically and the green-color FULL indicator is
illuminated at the service pane when the tank reaches the FULL level
selected for the configuration. If the fill/drain switch is returned to NORMAL,
the FULL indicator is extinguished started by opening the service panel door
on ground and turning the fill/drain switch to the FILL position.
DRAINING
Draining is started by opening the service panel door on ground and turning
the fill/drain switch to the DRAIN position. When the fill/drain switch is set to
DRAIN, the WWSC commands the following valves to open by supplying 28
VDC to the FILL/DRAIN valve, FWD DRAIN valve,FWD GRAY WATER
DRAIN valve (when installed), AFT GRAY WATER DRAIN valve (when
installed). The forward drain valve and the fill/drain valve open automatically
and enable water in the tank and tubing to be drained via the forward and aft
drain masts and the fill/drain nipple.
Electrical limit switches in each valve provides indication for the open and the
closed position.
The fill/drain switch also enables the forward drain valve to open during cold
weather conditions by overriding the safety thermostat inside forward drain
mast. At the service panel the indication DRAIN indicator light illuminates
indicating that all valves including the gray water drain valves are open.
If the fill/drain switch is returned to NORMAL, all valves close and the DRAIN
indication is extinguished.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
58
Developed for Training Purposes Only
The WWSC performs BIT tests of the following components: Level Sensor,
FILL/DRAIN valve, FWD DRAIN valve, FILL/DRAIN switch, FWD DRAIN
Mast, AFT DRAIN Mast, HOT BUS circuit. WWSC provides the following
signals to the water system indicators:
Developed for Training Purposes Only
Developed for Training Purposes Only
POTABLE WATER – SCHEMATIC DIAGRAM
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
59
STORAGE AND DISTRIBUTION – OPERATION ON ACFT EMB 195 WITH
FWD POTABLE WATER TANK AND WITHOUT IN-FLIGHT DRAINAGE
•
•
The VCU shares the power supply with the WWSC. It operates with the
aircraft 28 VDC power. The VCU is powered from one of three separate
sources: the aircraft DC GROUND SERVICE BUS, DC BUS 1 or HOT BUS 2
(battery). The VCU automatically switches to HOT BUS mode when both DC
GND SVC BUS and DC BUS 1 fail to supply power and the service panel
door is open. To preserve aircraft battery power, system operation in HOT
BUS mode is limited to potable and gray water valves operation and tank
level sensing for a maximum of six minutes. Each power input interface (DC
BUS 1, AC GND SVC BUS and HOT BUS) is protected with a 5 A aircraft
circuit breaker.
The fill/drain valve opens automatically and enables water in the tank and
hoses to be drained via the service panel in the aft section. The air
compressor turns on simultaneously to pressurize the water through the
water lines to the service panel.
At the service panel the DRAIN indicator starts blinking indicating that the
initial drain process is in progress.
Two minutes after the water tank is empty as detected by the water tank level
sensor, or 17 minutes after the air compressor started working the VCU will
turn-off the air compressor and send a signal to the WWSC to command the
following valves to open and drain the residual water by gravity:
POTABLE WATER FILL
The WWSC and VCU control the FILL process through inputs from the
fill/drain switch and water tank level sensor.
Filling is started by opening the service panel door on ground and turning the
fill/drain switch to the FILL position.
The fill/drain valve (2/2-way ball valve commanded by the WWSC), and the
overflow valve (2/2-way ball valve commanded by the VCU) are automatically
commanded to the OPEN position and enables water to be filled into the
water tank via the fill/drain nipple at the service panel. The opened overflow
valve enables tank ventilation and overflow via the forward drain port in case
of the water level sensor failure.
If the water tank becomes full as detected by the water level sensor, the
fill/drain valve and overflow valve close automatically and the FULL indicator
is illuminated at the service panel.
When the fill/drain switch is returned to NORMAL, the FULL indicator at the
service panel is extinguished.
It is also possible to interrupt the filling process before the water tank
becomes full by simply switching the fill/drain switch to the NORMAL position.
The fill/drain valve and overflow valve will close automatically.
•
•
•
•
POTABLE WATER DRAIN
On-Ground
Draining is started by opening the service panel door on ground and turning
the fill/drain switch to the DRAIN position. When the fill/drain switch is set to
DRAIN, the VCU commands the following valves to open:
FILL/DRAIN valve
Overflow valve
FWD DRAIN valve
FWD GRAY WATER DRAIN valve (when installed)
AFT GRAY WATER DRAIN valve (when installed)
In-flight DRAIN valve (when installed)
At the service panel the DRAIN indicator light illuminates steadily, indicating
that all the valves are open.
When the fill/drain switch is returned to NORMAL, all valves close and the
DRAIN indication is extinguished at the service panel.
The WWSC monitors the water tank level by means of the water tank level
sensor and sends an output signal to the VCU and to the aft FAP to indicate
the correct quantity.
IN- FLIGHT
The optional in-flight draining components and operation for the relocated
water tank system configuration is similar to the certified ERJ 190-200
configuration.
The only difference is that the residual water will be drained through the drain
port instead of the fwd drain mast.
The drain port incorporates the same protection feature provided by the drain
mast that opens the command to the fwd drain valve in case the temperature
of the drain port falls below 5°C, eliminating the risk of ice formation under
this condition.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
60
Developed for Training Purposes Only
Developed for Training Purposes Only
OPERATION
Developed for Training Purposes Only
Developed for Training Purposes Only
STORAGE AND DISTRIBUTION – OPERATION ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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61
WATER HEATER SYSTEM (38-12) – INTRODUCTION
A self-regulating water heater is installed in the lavatories to provide warm
water for hand washing, aimed at improving passenger comfort as well as
allowing the crew members to clean their hands, prior to beginning the food
servicing duties.
GENERAL DESCRIPTION
The water heater system works with the system that follows:
Water heater of the lavatory (AMM MPP 38-12-01/401).
COMPONENTS
Developed for Training Purposes Only
Developed for Training Purposes Only
•
WATER HEATER
A water heater in the potable water supply line provides warm water for hand
washing in the lavatory washbasins. The water heater is a cylindrical tank of
about 1.5 ℓ (0.40 gal.) capacity. It is located in the lavatory cabinet,
underneath the sink and installed in the supply line at the faucet. The water
heater tank consists of an inlet fitting, outlet fitting, and pressure relief valve.
The water heater electrical system consists of an ON-OFF toggle switch,
indicator light, manual reset thermostat (for overheat protection), temperature
controller, sensor, water-immersion cartridge heaters, and a water level
sensor. The water heater power rating is 210 W at 115 VAC, single phase,
400 Hz. Power is supplied from the AC GND SVC BUS. The water heater
circuit is protected by a tri-phase 7.5A circuit breaker in the LICC.
NOTE: The water heater does not provide a continuous hot water supply.
The maximum water temperature recovery time is 15 minutes with 15 - 18°C
(59 - 64 °F).
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WATER HEATER COMPONENTS
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63
Power is supplied by the AC GND (Ground) SVC (Service) BUS. It is
designed to operate with an air cushion at the top, under normal inlet water
pressure. This prevents damage to the water heater tank if freezing occurs. A
relief valve prevents excessive pressure buildup within the water heater tank.
The indicator light mounted on the water heater tank illuminates when power
is supplied to the cartridge heaters. The heaters provide warm water to the
lavatory washbasins. The manual reset thermostat is set to open the heater
circuit when the switch temperature is 72 - 82 °C (161 - 179 °F). The relief
valve prevents excessive pressure buildup within the water heater tank. The
pressure relief setting is 140 psi (965.27 KPa). During normal operation, the
manual reset thermostat remains closed and the water temperature is
maintained by the temperature control sensor at 49.4 - 53.8 °C (121 to 129
°F). If the temperature control sensor malfunctions, the water temperature
can rise to 76.7 °C ± 5 °C (170 °F ± 9 °F). The maximum water temperature
recovery time is 15 minutes with 15-18 °C (60-65 °F) initial water
temperature. When the water temperature is below the manual reset overtemperature switch trip point, the manual reset thermostat contacts remain
closed, the indicator light illuminates, and power is supplied to the heating
circuit. When the water temperature rises above the manual thermostat trip
temperature, the manual reset thermostat opens the heating circuit and the
indicator light goes out. Heating circuit power cannot be restored until the
water temperature falls below 48.9 °C (120 °F). When the water level falls
below the water level sensor, power is removed from the heater.
Temperature control at the water outlet is achieved by mixing cold and hot
water supplies in the lavatory faucet.
Developed for Training Purposes Only
Developed for Training Purposes Only
OPERATION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
Power is supplied by AC BUS 1.
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64
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Developed for Training Purposes Only
WATER HEATER SYSTEM - OPERATION
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
65
WATER TANK QUANTITY INDICATION (38-13)
INTRODUCTION
The water tank quantity indication subsystem includes components to
indicate and monitor the water level within the potable water tank. The
system is made up of water tank level sensor and service panel indication.
GENERAL DESCRIPTION
The water tank quantity indication works with the systems that follow:
Water tank level sensor (AMM MPP 38-13-02/401).
Service panel indication (AMM MPP 38-13-04/401).
Developed for Training Purposes Only
Developed for Training Purposes Only
•
•
COMPONENTS
WATER TANK LEVEL SENSOR
The level sensor operates as a variable capacitor using water in the tank as a
variable component. It provides a current signal proportional to the water
level inside the tank. The output signal increases if water level increases and
vice versa. The potable water tank level sensor is continuously monitored,
and the quantity is indicated at the FAP (Flight Attendant Panel). Input
voltage is 28 VDC (Volt Direct Current) nominal and is provided by the
WWSC (Water and Waste System Controller).
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66
WATER TANK QUANTITY INDICATION - MAIN COMPONENTS
EFFECTIVITY: ON ACFT BEM 195 WITH FWD POTABLE WATER TANK
Developed for Training Purposes Only
Developed for Training Purposes Only
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK
PRESSURE
SWITCH
PRESSURE OVERFLOW
PORT
PORT PORT
FLANGE
HOUSING
ELECTRICAL CONNECTOR
TOTAL LENGTH
451,5 mm (17.78 in)
SENSOR FLANGE DIAMETER
121,4 mm (4.78 in)
WEIGHT
0,47 kg (1.036 lb)
OPERATING VOLTAGE
28 VDC (+2,3 VDC / -1,0 VDC)
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67
SERVICE PANEL INDICATION
The service panel indication provides the tank “FULL” status and the open
position of the system drain valves during system servicing. Input power is 28
VDC and is supplied by the WWSC, which also controls the indicator lights.
The indicator panel is located in the potable water service panel and is
installed in the non-pressurized, non-temperature controlled fuselage skin
area.
The water tank quantity indication on the FAP is in the following figures 0, ¼,
½, ¾, and 1 in the percentage: 0%; 25%; 50%; 75%, 100%.
Developed for Training Purposes Only
Developed for Training Purposes Only
The WWSC also monitors the water tank level and sends an output signal to
the FAP, to indicate the correct quantity and to the service panel indication
LED (Light Emitting Diodes).
The WATER SERVICE FAULT message is provided to the FAP under the
following conditions:
•
•
•
•
•
•
Fill/Drain valve fails to CLOSE
FWD Drain valve fails to CLOSE
Aft Drain valve fails CLOSE
FWD or AFT Gray Water Drain valve fails to OPEN
Indicated temperature of the forward drain mast is continuously less than
15°C (59°F) for 5 minutes.
Indicated temperature of either drain mast is continuously greater than
120°C (248°F) for 2 minutes.
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
The service panel indication provides the tank “FULL” status and the open
position of the system drain valves during system servicing. Input power is 28
VDC and is supplied by the WWSC and VCU (Valve Control Unit), which also
controls the indicator lights. The indicator panel is located in the potable
water service panel and is installed in the non-pressurized, non-temperature
controlled fuselage skin area.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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Developed for Training Purposes Only
Developed for Training Purposes Only
WATER TANK QUANTITY INDICATION - MAIN COMPONENTS
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
69
OPERATION
The water tank level sensor acts as an electronic sensing probe and provides
a continuous measuring of the water level. The water tank quantity indication
on the FAP is in the following percentage figures: 0%; 25%; 50%; 75%,
100%. The aft FAP provides water quantity indication to the cabin attendant.
The service panel indication contains two green LEDs that are marked
“FULL” and “DRAIN”. Filling is started by turning the FILL/DRAIN switch to
the FILL position. The FILL/DRAIN valve is automatically commanded to the
OPEN position and enables water tank to be filled via fill/ drain nipple in the
service panel. If the water level sensor detects that the water tank is full, the
fill/drain valve automatically closes and the “FULL” indicator illuminates on
the service panel. When the FILL/DRAIN switch is returned to “NORMAL”
position, the valve closes and the “FULL” indication extinguishes on the
service panel. Draining is started by turning the FILL/DRAIN switch to the
“DRAIN” position. During servicing, a “DRAIN” green-color indication
illuminates in the service panel when the tank reaches the empty level
selected for the configuration. When the FILL/ DRAIN switch is returned to
“NORMAL”, all valves close and the “DRAIN” indication extinguishes on the
service panel.
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Developed for Training Purposes Only
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND
WWSC
EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND
WWSC
ABNORMAL OPERATION
A faulty water tank level sensor is detected by the WWSC. This failure occurs
if the output signal of the level sensor is out of range. The aft FAP provides
system fault indication to the cabin attendant and the service panel indication
is not available. The fill/ drain valve provides an overflow path to water when
the water level sensor is not operating. The valve is operated by electrical
signals from the WWSC.
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WATER TANK QUANTITY INDICATION – OPERATION EFFECTIVITY: AIRCRAFT WITH AFT POTABLE WATER TANK AND WWSC
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71
OPERATION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
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Developed for Training Purposes Only
ABNORMAL OPERATION
When the output signal of the level sensor is out of range, a faulty water tank
level sensor is detected by the WWSC. The aft FAP provides system fault
indication to the cabin attendant and the service panel indication is not
available. The overflow valve provides an overflow path to water when the
water level sensor is not operating. The valve is operated by electrical signals
from the VCU.
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WATER TANK QUANTITY INDICATION – OPERATION EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
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73
WASTE DISPOSAL (38-30)
INTRODUCTION
The waste disposal system provides waste collection and storage from the
toilet assemblies located within the lavatories and from the gray water
coming from the galley sinks and lavatory washbasins. The waste disposal
system is composed of two subsystems, the VWS (Vacuum Waste System)
and the gray water drain system. The VWS uses either a vacuum generator
or differential pressure between the cabin and the ambient to transport the
waste from the toilets to a vacuum waste system tank.
The WASTE DISPOSAL includes these subsystems:
• GRAY WATER – DRAIN SYSTEM (AMM SDS 38-31-00/1)
• VACUUM WASTE SYSTEM (VWS) (AMM SDS 38-32-00/1)
The Waste Disposal System transports waste and gray water from the
lavatories and galley to the waste tank and drain masts respectively.
Gray water from the lavatory and galley is drained through auto-drain valves
and directed to the drain mast of the aircraft. The auto-drain valves allow the
drainage of liquids on ground and in flight, without creating an objectionable
whistle, whine, or rush of air, and they also prevent loss of cabin air. These
valves are installed inside the respective galley or lavatory.
The Vacuum Waste System includes toilets located in the lavatories. Thinwalled waste lines connect the toilets to a single waste tank whose usable
capacity is 95ℓ (25 gal.), located between the aft left lavatory and the
pressure bulkhead, above the cabin floor level. The VWS uses differential
pressure to transport waste. The differential pressure is generated either by a
vacuum generator at low altitudes, below 5486 m (18000 ft), or naturally by
the difference in pressure between the aircraft cabin and the outside air.
Electrical power is available directly from the aircraft GND (Ground) SVC
(Service) bus. The control circuit of the MSR (Motor Starting Relay) is
controlled by the WWSC (Water and Waste System Controller). This
configuration allows performing a toilet flush without having to energize the
entire aircraft.
GRAY WATER - DRAIN SYSTEM (38-31)
The gray-water drain system allows the gray water to drain from the galleys
and lavatories to the aircraft drain masts. The gray-water drain system is
made up of the following equipments:
•
•
•
•
•
Gray water auto drain valves
Gray Water Drain Line
Lavatory Sump
Galley Sump
Drain Mast
IF APPLICABLE TO THE AIRCRAFT CONFIGURATION:
•
•
•
Gray Water Holding Tank
Gray Water Drain Valve.
Gray Water Ground Valve
VACUUM WASTE SYSTEM (VWS) (38-32)
The VWS (Vacuum Waste System) carries waste from the lavatories to the
waste tank using vacuum pressure.
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GENERAL DESCRIPTION
COMPONENTS
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Developed for Training Purposes Only
WASTE DISPOSAL - MAIN COMPONENTS EFFECTIVITY: ACFT WITH AFT POTABLE WATER TANK
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WASTE DISPOSAL - MAIN COMPONENTS EFFECTIVITY: ACFT WITH FWD POTABLE WATER TANK
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77
The waste lines for transporting the waste are installed inside the
pressurized, temperature-controlled environment of the fuselage and are
routed from the toilets to the vacuum system tank. Gray water hoses are
installed for the disposal of used water out of the lavatory and galley sinks.
During a toilet flush cycle, the vacuum waste system uses a small amount of
pressurized water from the potable water system to rinse the toilet bowl and
aid in the evacuation of waste. During ground servicing, the waste tank is
drained into a service truck through a drain valve, drain line, and service
panel. A rinse line routed from the service panel to a rotating rinse nozzle
within the waste tank is used to supply rinsing fluid to the tank. Level sensors
are mounted on the waste tank.
The air that carried the waste into the waste tank then passes through a
water waste separator to remove traces of moisture and waste and then the
air is exhausted through the aircraft exhaust plumbing, exiting to the aft of the
aft passenger door. A check valve is mounted in this exhaust line and serves
to prevent the backflow of air into the system when the vacuum generator is
operating. The check valve allows full airflow when the vacuum generator is
not used. The waste tank has sufficient “dead space” above the waste level
to assure that waste will not be expelled from the aircraft through the water
separator and exhaust plumbing.
VACUUM WASTE SYSTEM
The vacuum generator is a 115/200 VAC, 400 Hz motor operated unit. It has
two compressor stages for maximum efficiency and rapid startup. The unit
incorporates a 28 VDC (Volt Direct Current) thermally protected orbital flush
valve to allow the transport of waste from the toilet to a remote vacuum
system tank. The toilet also has a 28 VDC solenoid rinse valve for introducing
potable water into the bowl for rinsing. The potable water supply is protected
from contamination. The sequencing of the operation of the toilet components
is controlled by an FCU (Flush Control Unit).
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK
GRAY WATER DRAIN SYSTEM
When a sink of the galley or lavatory is drained, the auto-drain valve opens.
The gray water flows through the gray water hoses to the drain masts. The
drain masts lead the gray water away from the aircraft.
The waste is carried to the waste tank through tubing and enters the tank via
flow diverter that slows the waste down in order to minimize splashing and
turbulence in the waste tank. The vacuum waste tubing is installed in the
pressurized zone, under the cabin floor, attached at regular intervals with
padded saddle clamps attached to the floor beams. The waste line is
designed to minimize the number of bends to reduce the possibility of clogs,
thus preventing line blockages and associated maintenance actions. Periodic
cleaning of the waste lines with crushed ice and vinegar or chemical solution
is necessary to prevent build-up within the waste line, which could lead to
waste line clogs.
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OPERATION
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WASTE DISPOSAL – OPERATION EFFECTIVITY: ACFT WITH AFT POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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79
OPERATION
GRAY WATER DRAIN SYSTEM
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
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Developed for Training Purposes Only
The sinks of the galleys and lavatories are connected via the auto-drain
valves to the gray-water ground valve. The gray water ground valve serves to
direct the flow of gray water to the drain port on ground and to the fwd drain
mast in-flight. When the gray water enters the auto-drain valves from the
sinks, the gray-water ground valve opens and the water drains through the
drain masts when in-flight. When operating on the ground, the gray water is
drained by gravity through the drain port or the drain mast.
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WASTE DISPOSAL – OPERATION EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
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81
INTRODUCTION
GRAY WATER HOLDING TANK DRAIN SYSTEM
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK
EFFECTIVITY: AIRCRAFT WITH GRAY WATER HOLDING TANK
The gray-water drain system allows the gray water to drain from the galleys
and lavatories to the aircraft drain masts. The gray-water drain system is
made up of the following equipments:
• Gray-water hoses;
• Auto-drain valves;
• Drain mast;
• Gray water holding tank (if applicable to aircraft configuration)
DRAINING IN FLIGHT
In-flight drainage of the gray water system is commanded by the WWSC. The
WWSC opens and leaves open the gray water drain valve two minutes after it
detects that the landing gear is up. The normal position for the valve is OPEN
during a flight. In flight, the auto-drain valve remains in a closed position until
there is a head of gray water at the inlet; the auto-drain valve then opens
automatically in order to drain the used water.
GENERAL DESCRIPTION
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK AND
WITHOUT GRAY WATER HOLDING UNIT
The sinks of the galleys and lavatories are connected via the auto-drain
valves to the drain masts. Drain of the gray water is possible on the ground
during ground service or in flight via the drain masts. When gray water enters
the auto drain valves from the sinks, the valves open and the water is drained
through the drain masts.
DRAINING ON GROUND
The gray water tank provides gray water collection and storage to avoid
spillage while the aircraft is parked at the aircraft runway. The gray water
drain valve drains gray water on ground when commanded from the fill/drain
switch to drain position. When no differential pressure is applied (the aircraft
is on the ground), the valve drains and no residual water remains in the
valve. The valve remains open on ground.
Gray water auto drain valves are installed below the lavatories and galley
sinks. The valve drains the gray water through drain masts yet prevents the
loss of air through the empty and open sink. The design allows continuous
water drainage under small fluid heads and prevents back-flow. The valves
open at a maximum water head of 178 mm (7 inches). When no differential
pressure is applied, that is, when the aircraft is on the ground, the valve
drains gray water to drain masts and no residual water remains in the valve.
It is acceptable that the valve remains open on ground. In flight, the valve
remains in a closed position until there is a head of gray water at the inlet.
The valve then opens automatically in order to drain the used water.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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GRAY WATER - DRAIN SYSTEM (38-31)
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GRAY WATER - DRAIN SYSTEM – OVERVIEW ON ACFT WITH AFT POTABLE, WITHOUT GRAY WATER HOLDING UNIT
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GRAY WATER - DRAIN SYSTEM – OVERVIEW ON ACFT WITH FWD POTABLE WATER TANK, WITHOUT GRAY WATER HOLDING UNIT
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85
COMPONENTS
AUTO DRAIN VALVES
The auto-drain valves are installed above the floor in the gray water lines
inside the respective galley and lavatory. The auto-drain valves allow for
drainage of liquids on the ground and in-flight without creating objectionable
whistle, whine or rush of air, and prevent loss of cabin air. The auto-drain
valves are normally in the closed position.
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Developed for Training Purposes Only
GRAY WATER HOSES
Reinforced hoses above and below the floor are installed to carry the drain
water from the lavatory and the galley. In order to prevent clogs, the hoses
are installed at an angle as close to vertical as possible, with minimum
number of smooth bends.
DRAIN MASTS
The drain masts contain a heater (AMM SDS 30-72-00/1). The drain masts
are dual port drain ports. One port is used to drain the potable water and the
other is used to drain the gray water. The construction of the drain masts
ensures proper segregation between the potable and serviced water.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
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GRAY WATER - DRAIN SYSTEM – OVERVIEW ON ACFT WITH AFT POTABLE WATER TANK
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87
COMPONENTS
DRAIN PORT
The drain port is installed in the FWD fuselage. The drain port contains a
heater (AMM SDS 30-72-00/1). The drain port is used for drainage of potable
and gray water on the ground from FWD lavatory and galley and for in-flight
drainage of residual potable water when the in-flight drainage optional is
selected. The drain port has dual-ports. One port is used to drain the potable
water and the other is used to drain the gray water. The drain port contains a
flow detector to avoid noise generation from the drain tube during flight.
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Developed for Training Purposes Only
DRAIN MASTS
The drain masts contain a heater (AMM SDS 30-72-00/1). The aft drain mast
is dual port drain ports. One port is used to drain the potable water and the
other is used to drain the gray water. The construction of the drain masts
ensures proper segregation between the potable and serviced water. In the
forward drain mast one port is used to drain the gray water and another port
is plugged.
GRAY-WATER GROUND VALVE
The gray-water ground valve is used to direct the flow of gray water to the
drain port on the ground and to the FWD drain mast in flight. It is installed in
the FWD fuselage. This valve remains open when the aircraft is on the
ground and closed during flight.
The gray-water ground valve is operated by electrical signals from the VCU
(Valve Control Unit).
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88
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Developed for Training Purposes Only
GRAY WATER - DRAIN SYSTEM - MAIN COMPONENTS
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
89
OPERATION
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK AND
WITHOUT GRAY WATER HOLDING UNIT
When a sink of the galley or lavatory is drained, the auto-drain valve opens.
The gray water flows through the gray water hoses to the drain masts. The
drain masts lead the gray water away from the aircraft.
When a sink of the galley or lavatory is drained, the auto-drain valve opens.
The gray water flows through the gray water hoses to the drain masts or
drain port. The drain masts and drain port lead the gray water away from the
aircraft.
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Developed for Training Purposes Only
EFFECTIVITY: ON ACFT WITH FWD POTABLE WATER TANK
The gray-water ground valve is used to direct the flow of gray water to the
drain port on the ground and to the FWD drain mast in flight.
The WWSC opens and leaves open the following valves 2 minutes after it
detects that the landing gear is up. The valves are always closed while
landing gear is down except during the drain process.
•
•
FWD GRAY WATER DRAIN valve (on optional system only)
AFT GRAY WATER DRAIN valve (on optional system only)
The VCU commands the ground valve to open when the weight on wheels
signal becomes true. The ground valve will be commanded close by the VCU
180 seconds after the weight on wheels becomes false. The time delay was
introduced to ensure that the contents of the gray water tank are drained by
gravity through the drain port while still at low altitudes when cabin differential
pressure is low.
.
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
90
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GRAY WATER - DRAIN SYSTEM - MAIN COMPONENTS ON ACFT WITH FWD POTABLE WATER TANK
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
91
VACUUM WASTE SYSTEM (VWS) (38-32) – INTRODUCTION
The VWS (Vacuum Waste System) carries waste from the lavatories to the
waste tank using vacuum pressure.
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Vacuum Waste System Toilet Assemblies
Vacuum Waste System Flush Switch
Overboard Air Exhaust Line
Waste Water Separator
Vacuum Waste System Tank
Vacuum Generator
Waste Tank Rinse Nozzles
Vacuum Waste System Check Valve
Vacuum Waste System Tank Drain Valve
Waste Tank Level Sensors
Vacuum Waste System Service Panel Drain Valve
Vacuum Waste System Drain Valve Control Cable
Vacuum Waste System Rinse Nipple
Vacuum Waste System Service Panel Switch
Vacuum Waste System Drain Lines
Vacuum Waste System Lines
Vacuum Waste System Rinse Line
Motor Starting Relay
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
Developed for Training Purposes Only
Developed for Training Purposes Only
Vacuum waste system is made up of the following equipments:
92
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Developed for Training Purposes Only
GRAY WATER - DRAIN SYSTEM – OPERATION ON ACFT EMB 195 WITH FWD POTABLE WATER TANK AND WITHOUT GRAY WATER
HOLDING TANK
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93
GENERAL DESCRIPTION
The MSR (Motor Starting Relay) is used for control of the vacuum generator.
Electrical power for the vacuum generator is available directly from the
aircraft ground service bus. The control circuit of the motor starting relay is
controlled by the WWSC (Water and Waste System Controller). This
configuration allows the toilet to be flushed without energizing the complete
aircraft.
Developed for Training Purposes Only
Developed for Training Purposes Only
The vacuum waste system allows for the transport of waste from the lavatory
toilets to an aft-mounted vacuum waste system tank. Vacuum waste lines are
installed in the pressurized zone under the cabin floor. The VWS uses
differential pressure to transport waste. The differential pressure is either
generated by a vacuum generator at low altitudes, below 5486 m (18000 ft),
or naturally by the difference in pressure between the aircraft cabin and the
outside air. The waste lines, vacuum waste system tank and waste drain line
are all designed and qualified to take into account the maximum pressure
differentials in order to ensure safe operation and prevent damage in flight.
Waste-tank level sensors are installed on the vacuum waste system tank.
The waste-tank level sensors uses the WWSC to send a signal to the flight
attendant panel that servicing of the waste tank is required soon, “SERVICE
TANK“. The second level sensor sends a signal that the tank is full “TANK
FULL”. Once the aircraft has landed, the waste tank is drained through a
single waste service panel.
Gasket type heaters installed under the VWS service panel drain valve and
VWS rinse nipple prevents liquid from freezing in the lines (AMM SDS 30-7400/1).
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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94
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VACUUM WASTE SYSTEM (VWS) - OVERVIEW
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
95
COMPONENTS
VACUUM WASTE SYSTEM TOILET ASSEMBLY
The VWS toilet assembly consists of a solenoid rinse water valve and
strainer, FCU (Flush Control Unit), flush ring, anti-siphon valve, and
supporting frame.
The flush ring assembly is fitted with spray nozzles and is mounted on the
upper rim of the bowl. The inlet of the ring is connects to the anti-siphon
valve.
The VWS toilet is securely mounted to the sealed lavatory floor pan. It
connects to the aircraft electrical supply through an electrical connector and
to the water supply with a compression type fitting on the rinse assembly.
VACUUM WASTE SYSTEM LAVATORY FLUSH SWITCH
Toilet flushing is initiated by a passenger pushing the momentary contact
type flush switch located inside the lavatory. The toilet FCU mounted on the
toilet sequences the operation of the vacuum toilet and reports any faults
through the WWSC to the CMC (Central Maintenance Computer).
The anti-siphon valve is designed to prevent contamination of the aircraft
potable water supply by breaking contact of the fluid and providing an air gap
which prevents reverse flow from the bowl.
Rinse water is supplied to the anti-siphon valve by the rinse valve. The rinse
valve is a solenoid-controlled, self-contained unit. The valve incorporates a
screen and an integral water inlet for the aircraft interface.
The flush control unit (FCU) is a modular electronic assembly mounted on
the toilet support pedestal. A discrete logic circuit inside the FCU monitors
and controls operation of the toilet by timing and sequencing various
components during the flush cycle. The FCU is electrically connected to the
flush switch, rinse valve assembly and aircraft blower control module. A
maintenance switch mounted on the FCU permits operation of the flush valve
and blower operation of the flush valve and blower for ground maintenance.
A label on the FCU provides instructions for using the switch.
Each toilet assembly is self monitoring and outputs a signal if the flush valve
is obstructed.
The toilet rinse valve operates on 28 VDC (Volt Direct Current) power. The
toilet uses a 28 VDC orbital flush valve with dual face seals to prevent odors
from migrating into the cabin during shutdowns of the aircraft. This valve
contains switches at both open and closed positions to make sure that in the
open position, the valve is fully open with no obstruction into the waste
stream.
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96
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Developed for Training Purposes Only
The toilet bowl is fabricated of stainless steel with a non-stick coating applied
to the inside surface. Mounted at the top rim of the bowl is the flush ring
assembly.
The toilet assembly is provided in two configurations for left-hand and righthand installations.
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM (VWS) - BLOCK DIAGRAM
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97
OVERBOARD AIR EXHAUST LINE
The overboard air exhaust lines, which connect to the waste water separator
and vacuum generator, allow air to be expelled from the system. The exhaust
line extends from the VWS tank to the exterior of the aircraft. A check valve is
mounted in the exhaust line to prevent the backflow of air into the system
when the vacuum generator is operating, but allows full airflow when the
vacuum generator is not in use.
The waste water separator connects to the aircraft vent tubing with a beaded
end. It is composed of two separate subassemblies: the water separator is
positioned within the waste holding tank and the filter housing is positioned
above the tank. This design permits easy removal of both pieces of the
assembly within the limited space available above the waste tank. It also
maximizes the useful tank capacity by minimizing the protrusion of the
separator within the tank. The filter housing includes an internal mesh that
must be removed and cleaned during the maintenance intervals.
VACUUM GENERATOR
The two-stage centrifugal flow vacuum generator, located above the VWS
tank, is powered by a 3-phase 115/200 VAC at 400 Hz from LICC (Left
Integrated Control-Center). The vacuum generator runs for 10 seconds
during each flush cycle. This compact unit has compressor stages mounted
to a shaft. There are triple redundant, thermal switches are wired in series
with the service panel door switch and motor starting relay through the
WWSC. This inhibits power application to the vacuum generator if an
overheat condition exists. The aircraft itself provides additional protection
against over-current conditions. Mounting provisions for the vacuum
generator are provided on the aircraft structure, just above the VWS tank.
The unit is attached to three vibration mounts that are in turn mounted to a
rigid aircraft mount. The orientation of the unit is controlled to prevent
moisture accumulation in the unit.
The water separator has an orifice at the outlet to limit airflow. This feature
guards against contamination exhausted from the aircraft and limits the
airflow through the system, should the toilet flush valve fail in the open
position.
VACUUM WASTE SYSTEM TANK
The vacuum waste system tank is located between the aft left lavatory and
the pressure bulkhead, above the cabin floor level. The tank has a 95 ℓ (25
gal.) usable capacity. This capacity allows for a 5.5-hour flight at maximum
passenger loading with draining, rinsing and pre-charging performed after the
flight. Alternatively, for shorter flights, the tank can be serviced after every
other flight. The thin-walled welded tank is smooth and completely sealed on
the inside surface to prevent the escape of liquid waste or vapor to the
outside.
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98
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WASTE WATER SEPARATOR
The waste water separator, mounted on the waste tank, removes entrained
moisture from the air stream which carries the waste into the waste tank. This
ensures that no contamination is passed through the vacuum generator or
exhausted from the aircraft through the vacuum exhaust plumbing.
The tank will withstand steam cleaning and repeated vigorous scrubbing with
any commonly used cleaning agent. It will also resist the impact loads
caused by heavy solid objects that may be flushed into the waste system.
The tank is constructed to withstand a proof pressure of 345 KPa (50 psig), a
proof vacuum pressure of 87 KPa (12.6 psig), a burst pressure of 517 KPa
(75 psig) and a collapsing vacuum differential pressure of 116 KPa (16.8
psig).
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
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99
VACUUM WASTE SYSTEM CHECK VALVE
The self-contained check valve, located in the overboard air exhaust line,
prevents backflow of ambient or vacuum exhaust air into the toilet system. It
contains dual flapper doors that allow only one way airflow. The check valve
is installed parallel with the vacuum generator. It serves to bypass airflow
when the vacuum generator operation is not required at altitudes above 5486
m (18000 ft). The check valve has a vacuum proof pressure of 87 KPa (12.6
psig) and a positive proof pressure of 138 KPa (20 psig).
VACUUM WASTE SYSTEM TANK DRAIN VALVE
The tank drain valve is bolted between the VWS tank flange and the drain
line flange. Internally, the tank drain valve contains two seals, one on the inlet
and one on the outlet, to ensure that no waste products are allowed to leak
from the waste tank. The inside flange of the tank drain valve is valve is
contoured to prevent the accumulation of any residual liquid within the valve
after tank draining. The valve is mounted at an angle to prevent waste from
remaining in the valve after draining. The valve contains a handle, connected
to the service panel by the VWS drain valve control cable.
WASTE-TANK LEVEL SENSOR
The two waste-tank level sensors, located on the VWS tank, detect liquid on
the sensing surface. This sensing surface is coated with a material that
prevents the buildup of waste. They are strategically located in the tank to
sense fluid that reaches a capacity of seventy-five percent. The seventy-five
percent indication point is used to notify the crew that servicing will be
required soon. The waste-tank level sensors are electrically connected to the
WWSC to transmit a seventy-five percent or "FULL" signal. The LICC is
powered by the aircraft 28 VDC power supply through the WWSC.
During toilet operation on the ground and at low altitudes, the air flows
through the vacuum generator to the overboard vent. At altitudes above
18000 ft (5486 m), the airflow bypasses the vacuum generator through the
check valve to the overboard vent. The check valve housing contains a
sealed double flapper assembly, with the flapper doors normally spring
loaded in the closed position to prevent internal leakage. The check valve
relies on the mating surface between the flappers and the valve housing to
create the seal.
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100
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VACUUM WASTE SYSTEM RINSE NOZZLE
The rotating VWS rinse nozzle, mounted on the waste tank, uses a machined
spinning element that rotates when water pressure is applied from the
service cart. The self-cleaning nozzle is bolted to the waste tank and sealed
with an O-ring. Once it is located on the top of the tank to achieve optimum
cleaning of the parts, preventing contamination. The spinning rinse nozzle
uses the principle of water bearing where water pressure acts as a lubricant
between the rotating nozzle and its shaft, which allows free rotation of the
nozzle. The nozzle is designed to cleanse the tank inner walls, liquid level
sensors, flow diverter, and outside housing of the waste water separator. It is
also used to supply pre-charge fluid to the waste tank. The rinse nozzle has
an inlet for connection to the rinse hose assembly.
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
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101
VACUUM WASTE SYSTEM DRAIN VALVE CONTROL CABLE
The drain valve control cable is used to translate the push/pull motion from a
handle mounted on the service panel to rotational movement of the tank drain
valve closure element. The control cable is flexible so that it can be routed in
a convenient way. It is supported along its length by P-clamps and is rigidly
mounted to a bracket near the drain valve handle to guarantee correct
alignment. A clevis on the control cable connects to the VWS tank drain
valve.
VACUUM WASTE SYSTEM SERVICE PANEL SWITCH
The service panel switch, located on the service panel, signals the WWSC to
inhibit operation of the waste system when the VWS service panel is opened.
If the service panel door switch contacts are detected to be open while the
WOW (Weight-on-Wheels) condition is true and the aircraft is not moving, the
WWSC disables all toilets FCU and prevents MSR operation. The
electromechanical type service panel switch contains a spring-loaded plunger
that has a pre-travel of 1 mm (0.04 in) and a minimum over travel of 6 mm
(0.25 in). The contacts are closed when the service panel door is closed, to
enable the system.
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM SERVICE PANEL DRAIN VALVE
The service panel drain valve, located on the waste service panel, is used to
drain the vacuum waste system tank. The service panel drain valve is located
in the waste service panel. The service panel drain valve contains a lever
lock cap that hooks onto the valve body. It remains closed by an over-center
locking design. The cap remains open by gravitational force to allow easy
connection of the drain line. The inboard end of the adapter contains a fitting
for attachment with the drain line that extends from the service panel to the
vacuum waste system tank.
VACUUM WASTE SYSTEM RINSE NIPPLE
The rinse nipple, located on the waste service panel, connects to the rinse
hose and serves as an overboard connection to allow rinsing of the VWS
tank. The rinse nipple contains a lever lock cap that hooks onto the nipple
body and remains closed by an over-center locking design. The cap remains
open by gravity. The nipple is a different size from the water service panel
fill/drain nipple to prevent servicing errors. The inboard end of the adapter
contains a 19 mm (3/4 in) threaded fitting for attachment of the rinse hose.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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102
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VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
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103
WASTE SERVICING
WASTE DRAINING
The waste tank draining procedure is described as follows:
• Prepare the rinse solution as follows:
Put 44 - 46 ℓ (11.6 - 12.2 gal.) of water in a separate container and add one of
the germicidal deodorants that follow:
•
•
•
•
•
•
•
•
•
Push drain cable handle to close ball valve (primary)
Pre-charge tank with 1.6 to 2.1 US Gallons (6 to 8 liters) of rinse fluid
Turn off rinse fluid supply
Disconnect drain and rinse hoses
Close drain valve cap and rinse nipple cap
Clean surface of panel to remove spillages
Close and latch service panel door
Developed for Training Purposes Only
Developed for Training Purposes Only
•
For deodorant SANI-PAK POWDER SP77000 SERIES, add 44 - 46 g (1.5
- 1.6 oz) of germicidal deodorant.
For deodorant SANI-PAK LIQUID SP97000 SERIES, add 192 ml of
germicidal deodorant.
For MIRABOWL Q, add 1.092 kg (38.5 oz) of germicidal deodorant.
NOTE:
• Make sure that the waste tank is completely drained before you start to
supply the rinse fluid.
• If you do not use the correct rinse pressure you will not clean the level
sensors properly.
NOTE: You can use only water to do the waste tank servicing, but we
recommend the use of a rinse solution. The rinse solution contains
surfactants that help clean the inner surface of the waste tank.
NOTE: For aircraft that operate at temperatures below 0 °C (32 °F), add to
the rinse solution an anti-ice product according to the AMS 1424 and AMS
1428.
•
Open the drain valve cap and connect the drain hose (GSE 050 lavatory
dumping coupling)
NOTE: Contaminated water can stay between the waste drain valve and the
protective cap. Open carefully to prevent health problems.
•
•
Open the rinse nipple cap and connect the rinse hose (GSE 050 lavatory
filling coupling)
Push drain valve lever to open drain inner flapper (secondary drain)
NOTE: When you pull the drain control handle (2) a stiff condition can occur.
The maximum load for the drain control handle actuation should be
25.4 kgf (56 lbf).
•
•
Pull drain cable handle to open ball valve (primary) to drain waste tank
After waste tank has drained, start rinse fluid supply and rinse tank for two
minutes minimum. Start to supply the rinse fluid through the GSE 051 at a
pressure of 20 to 50 psi for 2 min or until a volume of 38 ℓ (10 gal.) is
used.
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VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
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105
VACUUM WASTE SYSTEM LINES
The VWS lines are preformed sections of tubing used to transport waste from
the vacuum toilets to the waste tank. The lines are routed under the cabin
floor in the most direct path possible to reduce the chance of waste blockage.
The VWS lines are made of straight sections that use a thicker wall than
curved sections due to the thinning of the tubing when bent. Each tube is
outfitted with an O-ring ferrule on both ends, and the tube sections are
interconnected with clamshell-type couplings, which allow for quick assembly
and disassembly of the piping system.
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM DRAIN LINES
The VWS drain line extending from the VWS tank to the service panel is
constructed of three separate tube segments. It slopes downward and
forward of the VWS tank to meet with the service panel for through draining
and minimum drain line weight. The drain line connects to an adapter
mounted on the VWS tank drain valve with a clamshell type connection and
to the VWS service panel. Padded clamps support it along its length.
VACUUM WASTE SYSTEM RINSE LINE
The VWS rinse line, located between the VWS tank and VWS service panel,
transports rinse fluid from the VWS service panel rinse nipple to the VWS
tank rinse nozzle. The rinse line is clamped to support brackets on the
aircraft structure using P-clamps.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
106
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Developed for Training Purposes Only
WATER/WASTE - MAIN COMPONENTS
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The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
107
MOTOR STARTING RELAY
Developed for Training Purposes Only
Developed for Training Purposes Only
The motor starting relay, located under the cabin floor in the middle of the
fuselage, is used for control of the vacuum generator and to supply 115/200,
3-phase VAC electrical power. The hermetically sealed motor starting relay
uses a 28 VDC control circuit, actuated by the WWSC when the aircraft
altitude is below 18000 ft (5486 m). A secondary 28 VDC contact is
monitored by the WWSC to determine whether the motor starting relay has
failed in the closed position. Mounting provisions for the motor starting relay
are provided in the center avionics compartment. The unit is mounted within
a dedicated gasket enclosure with pass-through for the aircraft wiring.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
108
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VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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109
OPERATION
•
When the flush switch is pushed, approximately 0.2 ℓ (7.1 oz) of water is
introduced into the toilet bowl through the rinse valve. This will rinse the
bowl and aid in waste evacuation.
•
If the aircraft is below 5486 m (18000 ft), the WWSC powers the motor
starting relay to operate the vacuum generator. This creates a pressure
differential that transports the waste to the VWS tank. At higher altitudes,
the differential pressure between the cabin and ambient is sufficient to
transport the waste.
•
As the rinse valve closes, the toilet flush valve is opened for four seconds
and waste is evacuated to the VWS tank.
•
Ten seconds after the flush switch is pressed, the vacuum generator is
disabled (if at low altitude) and the toilet is ready to be flushed again.
The air that carries the waste into the VWS tank passes through a waste
water separator to remove traces of moisture and waste. This air is then
forced through the aircraft exhaust plumbing and exits through the aircraft
skin. A check valve is mounted in this exhaust line to prevent the backflow of
air into the system when the vacuum generator is operating and allows full
airflow when the vacuum generator is not in use. The waste tank has a
sufficient amount of empty space above the maximum waste level to ensure
that waste will not be expelled through the exhaust plumbing.
GROUND SERVICING
VWS tank draining is performed by a ground service technician. Draining
starts when the waste system service panel is opened. A switch on the
service panel inhibits system operation when the door is open. This
eliminates the potential spillage of waste on ground service personnel or
unintended operation of the vacuum generator. The service panel drain valve
and drain valve control cable handle connect to the waste tank drain valve
located at the outlet of the waste holding tank. Service cart drain and rinse
hoses are connected to the service panel equipment and both the service
panel drain valve and under waste tank drain valve are opened to drain the
waste tank. The service panel drain valve is controlled by a lever, mounted
on the valve. The under tank drain valve is controlled by a cable that has a
handle mounted on the service panel. Once the tank is fully drained, rinsing
fluid is introduced into the tank from the service panel through the rinse hose
and to a rotating rinse nozzle within the waste tank. After the tank is cleaned,
the service cart equipment is disconnected, the service panel valves are put
in their closed positions, and the service panel door is closed thereby
actuating the service panel switch and enabling the vacuum waste system.
Two ultrasonic point level sensors failure are monitored through continuing
WWSC BIT (Built-in Test) input. One level sensor is mounted at the 75%
level and is used to inform the crew members through the WWSC to the FAP
(Flight Attendant Panel) that servicing of the waste tank is required soon. The
second level sensor is mounted at the tank “FULL” level. This sensor is used
to signal to the WWSC that the waste tank is full, which then causes the
WWSC to disable the vacuum toilets and the MSR and turn on the TANK
FULL indication at the FAP. If the “FULL” level sensor is faulty, control logic
within the WWSC automatically shifts the “FULL” indication to the 75% level
sensor.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
110
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Developed for Training Purposes Only
The toilet flushes when a passenger pushes the flush switch. The toilet FCU,
mounted on the toilet, times and sequences the operation of the vacuum
toilet in the following order:
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Developed for Training Purposes Only
VACUUM WASTE SYSTEM (VWS) - MAIN COMPONENTS
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
111
CLOG IN THE TOILET
In case of a clog in the toilet outlet the toilet may be cleared on the ground by
a service technician. The toilet outlet is designed to be the smallest diameter
passage so that any objects that pass the toilet will travel all the way to the
waste tank and so that any item that could possibly become trapped in the
waste line will be easy to access at the toilet bowl. The toilet also includes a
maintenance switch that places the flush valve in the open position when
pressed and will operate the vacuum generator for 10 seconds when pressed
again and held for 2 seconds. This feature also allows easy manual removal
of any clogged object by holding the flush valve open. If manual clearing is
not possible, operating the vacuum generator will assist in clearing of the
waste lines of obstructions.
Developed for Training Purposes Only
Developed for Training Purposes Only
ABNORMAL OPERATION
VACUUM WASTE SYSTEM TANK BECOMES FULL
If the vacuum waste system tank becomes full, a waste-tank level sensor
notifies the WWSC to disable the toilets, preventing further flushing and overfilling of the waste tank.
TOILET RINSE VALVE WATER LEAK
In case of a toilet rinse valve water leak as may be caused by excessive
mineral deposits or other contamination, the lavatory water system may be
isolated by means of the manual shut-off valve supplied with the water
system within the lavatory compartment. The valve is clearly placarded and
readily accessible by the flight attendant without the use of tools.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
112
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THIS PAGE INTENTIONALLY LEFT BLANK
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113
AIR SUPPLY (38-40)
INTRODUCTION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
EFFECTIVITY: ON ACFT WITH AFT POTABLE WATER TANK
The potable water system is pressurized by bleed air coming from the APU
or the main engines or the air compressor. The air is introduced via an air
manifold into the water tank to provide regulated pressurized potable water.
GENERAL DESCRIPTION
The air is routed aft through the fuselage and connects to the air manifold in
the aft section. The air is introduced via an air manifold into the potable water
tank to provide regulated pressurized potable water. The air manifold
includes a shuttle valve, regulator, air filter, check valve and pressure relief
valve. The bleed air supply is connected to the shuttle valve. The bleed air is
filtered and regulated to the system operating pressure of 36 to 41 psig.
Alternately, as an optional feature, an air compressor is used to pressurize
the water system. In case the A/C is on the ground with the engines or APU
not running, or if the bleed air pressure is below the optimal range during
flight, the pressure switch mounted to the water tank signals the WWSC,
which activates the compressor to achieve the required water system
pressure.
The air is routed forward through the fuselage and connects to the air
manifold in the forward fuselage section. The air manifold includes a shuttle
valve, regulator, air filter, check valve and pressure relief valve. The air
manifold regulates the incoming air pressure to the working pressure level.
The bleed air supply is connected to the shuttle valve. The air compressor
has the overheat protection.
The air compressor is provided to improve the pressure stability of the
system when bleed air pressure is insufficient. The air compressor cycling is
controlled by the VCU (Valve Control Unit) based on the signal from the
pressure switch that is directly mounted to the water tank.
The vent valve is installed in the overflow line to allow proper venting of the
tank and avoid a buildup of vacuum during the gravity drainage when
operating on ground in the HOT BUS mode.
TRAINING INFORMATION POINTS
SNL 170-38-0008
190-38-0009
NOTE:
Because of water tank pressurization and water displacement from the tank
to the water lines, it is possible for the level indication to drop from 1 to ¾
immediately after servicing.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
114
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The bleed air pressure is used as the primary pressure source of the system.
The potable water system is pressurized by bleed air coming from the APU
(Auxiliary Power Unit) or main engines.
Developed for Training Purposes Only
Developed for Training Purposes Only
VACUUM WASTE SYSTEM (VWS) - OPERATION
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
115
COMPONENTS
SHUTTLE FUNCTION
Two inlet ports are connected to the air manifold: One to the bleed air from
the engines/APU and the other to the compressor. When air pressure is
applied to any one of the inlet ports, the valve closes the inlet port with the
lower pressure. The shuttle valve opens at a maximum pressure of 2 psig.
PRESSURE SWITCH
EFFECTIVITY: ON ACFT WITH AIR COMPRESSOR
The pressure switch is mounted on the top of the water tank. The pressure
switch monitors the pressure inside the tank. It gives a signal to the WWSC
(Water and Waste System Controller), when the pressure decreases to
below the required pressure.
The pressure switch has a membrane to monitor the difference between the
cabin pressure and the tank pressure.
If the compressor is not installed, the pressure switch port on top of tank
flange, where the pressure switch is threaded, is capped by a plug.
NON-RETURN (CHECK) FUNCTION
A check valve is used in the line between the air filter and regulator. The
check valve makes sure that the compressed air flows only in the direction of
the water tank. This valve opens as soon as the pressure of the inlet exceeds
the outlet pressure by 1.5 psig. When the differential pressure drops below
this value, the valve closes to prevent water from entering the compressed air
system.
PRESSURE REGULATING
At an inlet pressure of 44 to 59.4 psig the pressure is regulated between 36
psig and 41 psig to the cabin pressure. The maximum short-term bleed air
pressure that the manifold can withstand is 250 psig.
AIR HOSES
Air hoses are installed to supply the pressurized air. The air hoses are
clamped to support brackets on the aircraft structure.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
116
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Developed for Training Purposes Only
AIR MANIFOLD
The air manifold is installed in the compressed air line to regulate the
compressed air supply to the potable water system. The air manifold contains
a relief valve, a pressure regulator, an air filter, a non-return valve and a
shuttle valve. All functions are combined in one housing so only two inlet
ports and one outlet port have to be connected to the aircraft. One inlet is
connected to the bleed air system line and if applicable to the aircraft
configuration the other inlet line can be connected to the compressor
assembly.
Developed for Training Purposes Only
Developed for Training Purposes Only
AIR SUPPLY - OVERVIEW
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
117
COMPONENTS
PRESSURE SWITCH
EFFECTIVITY: ON ACFT WITH AIR COMPRESSOR
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
AIR COMPRESSOR
Developed for Training Purposes Only
Developed for Training Purposes Only
The pressure switch is mounted on the top of the water tank. The pressure
switch monitors the pressure inside the tank. It gives a signal to the VCU for
Embraer 195, when the pressure decreases to below the required pressure.
The pressure switch has a membrane to monitor the difference between the
cabin pressure and the tank pressure.
The air compressor is connected to the potable water tank via the air
manifold. For the on-ground drainage, the compressor pressurizes the water
line and drains the water through the service panel. The air compressor is
energized during ground servicing to allow the drainage in the aft section at
the service panel. Pressurized drainage is not enabled in the HOT BUS
mode. In this mode, all valves open and the potable water is drained on the
ground by gravity through the forward drain port, the aft drain mast, and the
fill/drain nipple. The compressor is activated by the VCU when water tank
pressure switch indicates low pressure, except when the fill or drain signal is
active while the aircraft is parked on the ground.
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
VENT VALVE
The vent valve is added in the overflow line. This valve is installed to allow
proper venting of the water tank.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
118
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Developed for Training Purposes Only
AIR SUPPLY - MAIN COMPONENTS – ON ACFT WITH AFT POTABLE WATER TANK AND WITHOUT AIR COMPRESSOR
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
119
OPERATION
PRESSURIZATION ON GROUND/FLIGHT
Regulated bleed air is supplied from the APU or the main engines via the air
manifold to the potable water tank. The air pressure forces the water from the
potable water tank through the water hoses to the different outlets. The air
manifold regulates the air pressure.
The air compressor can operate continuously when required. Power for the
pump is supplied by a self-contained 0.4 horsepower, three-phase, 400 Hz,
115/200 V motor. The air filter removes impurities from the compressed air
before entering the potable water tank. The air compressor is deenergized
during ground servicing to avoid unnecessary cycling.
The WWCS will disable the compressor under the following conditions:
•
•
•
•
•
Relief function
Pressure regulating
Filtration
Shuttle function
Non-return function
The air filter removes impurities from the compressed air before entering the
potable water tank. A check valve prevents water from entering the air lines.
An air pressure relief function is integral part of the air manifold and prevents
overpressure in the water system.
AIR COMPRESSOR
EFFECTIVITY: ON ACFT WITH AIR COMPRESSOR
The air compressor is provided to improve the pressure stability of the
system when bleed air pressure is insufficient. The air compressor cycling is
controlled by the WWCS, based on the signal from the pressure switch that is
directly mounted to the water tank. The compressor is switched on if the
bleed air pressure is too low. The low pressure set point is 35 ±1 psig and the
high pressure set point is 38 ±1 psig. The compressor supply line is
connected to the second port of the shuttle valve.
•
•
•
Service panel switch is in FILL or DRAIN position, AND;
Weight on wheels condition is TRUE, AND
Aircraft speed not greater than 4 kts
AIR COMPRESSOR ABNORMAL OPERATION
Air compressor or pressure switch abnormal operation is detected if the
pressure switch does not indicate pressure within 32 minutes. This condition
can also be the result of a leak. The FAP (Flight Attendant Panel) water fault
indication light will be illuminated. The abnormal operation message is
displayed on the CMC (Central Maintenance Computer).
The air compressor will be inhibited if the Fill/Drain valve fails to OPEN. The
FAP water fault indication light will be illuminated (blinking. The abnormal
operation message is displayed on the CMC.
Motor overheat protection is provided so that excessive temperatures will not
occur. When the coil has cooled sufficiently, the device is reset and the motor
is re-energized.
The compressor does not require any lubrication maintenance of the
bearings or cylinder bore.
The compressor is activated by the pressure switch via the WWCS.
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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120
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The individual functions of the air manifold are the following:
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Developed for Training Purposes Only
AIR SUPPLY - MAIN COMPONENTS – ON ACFT WITH AFT POTABLE WATER TANK AND AIR COMPRESSOR
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer
121
OPERATION
EFFECTIVITY: ON ACFT EMB 195 WITH FWD POTABLE WATER TANK
AIR COMPRESSOR
The VCU activates the air compressor when water tank pressure switch
indicates low pressure except when the FILL signal is active while the aircraft
is parked on the ground.
The compressor is also commanded ON by the VCU during the pressurized
drainage
The air compressor is provided to improve the pressure stability of the
system when bleed air pressure is insufficient. The air compressor cycling is
controlled by VCU on EMB 195, based on the signal from the pressure switch
that is directly mounted to the water tank. The compressor is switched on if
the bleed air pressure is too low. The low pressure set point is 35 ±1 psig and
the high pressure set point is 38 ±1 psig. The compressor supply line is
connected to the second port of the shuttle valve.
The air compressor will be inhibited if the Fill/Drain valve fails to OPEN. The
FAP water fault indication light will be illuminated (blinking) and for the EMB
195 the VCU fault indication light will be illuminated. A faulty Fill/Drain valve
has been detected by the VCU. The abnormal operation message is
displayed on the CMC.
Motor overheat protection is provided so that excessive temperatures will not
occur. When the coil has cooled sufficiently, the device is reset and the motor
is re-energized.
The compressor does not require any lubrication maintenance of the
bearings or cylinder bore.
The compressor is activated by the pressure switch via the VCU for the EMB
195.
The air compressor can operate continuously when required. Power for the
pump is supplied by a self-contained 0.4 horsepower, three-phase, 400 Hz,
115/200 V motor. The air filter removes impurities from the compressed air
before entering the potable water tank. The air compressor is deenergized
during ground servicing to avoid unnecessary cycling.
The VCU for EMB 195 will disable the compressor under the following
conditions:
•
•
•
Service panel switch is in FILL or DRAIN position, AND;
Weight on wheels condition is TRUE, AND
Aircraft speed not greater than 4 kts
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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122
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EFFECTIVITY: ON ACFT WITH AIR COMPRESSOR AIR COMPRESSOR
OPERATION
AIR COMPRESSOR ABNORMAL OPERATION
Air compressor or pressure switch abnormal operation is detected if the
pressure switch does not indicate pressure within 32 minutes. This condition
can also be the result of a leak. The FAP (Flight Attendant Panel) water fault
indication light and VCU for the EMB 195 fault indication light will be
illuminated. The abnormal operation message is displayed on the CMC
(Central Maintenance Computer).
Developed for Training Purposes Only
Developed for Training Purposes Only
AIR SUPPLY - OPERATION – ON ACFT WITH FWD POTABLE WATER TANK
Copyright 2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
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123
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Developed for Training Purposes Only
EMBRAER
Empresa Brasileira de Aeronáutica S.A.
Customer Training
Phone: +55 (12) 3927-5827
Fax: +55 (12) 3927-7535
http://www.embraer.com.br
2015 by EMBRAER – Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not be copied or reproduced in whole or in part, In any form or by any means without the express written Authorization of Embraer.
E-mail:Copyright
training@embraer.com.br
The information, technical data, designs and drawings disclosed in this document are proprietary information of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer