UnivYork/GC-MS/Terpine/001
Atmospheric Research Aircraft
TECHNICAL SPECIFICATION OF SCIENTIFIC EQUIPMENT
Technical Specification Number: From organisation [UnivYork/GC-MS/Terpine/001]
Title:
Name of Rack/Equipment [GC-MS Terpine Rack]
Issue:
Version number of THIS Issue. This number changes
each and every time the document is altered.
Date:
Date of THIS Issue [DD/MM/YYYY]
Equipment Part Number(s):
Part numbers of the rack/equipment. This could also
include Rack mounted equipment, Inlets, Sensor etc.
[ARA-XX-XXXX]
[LIF/INLET/001]
Summary
This document provides the technical specification of the installation of the [three-channel broad
band cell enhanced absorption spectrometer onto a standard equipment rack for use on the BAe146 Atmospheric Research Aircraft.] Explain any abbreviations used in the title of the
equipment here.
Document History
Reference to previous Issues of this TSSE (if applicable)
[CAM/BBCEAS/001, draft initial issue, 02/11/2009]
[CAM/BBCEAS/002, issue 1, 27/11/2009]
Specification Compiled by:
NAME
ADDRESS (of organisation)
Contact email address:
Contact phone number:
Signed:
Author of document
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UnivYork/GC-MS/Terpine/001
1.
SUMMARY OF CHANGES
Changes made at this Issue:
Added datasheet for XX equipment in Appendix X
Correction to Wiring Schematic diagram in page/Section X
Updated C of G table in page/section X
Circuit breaker of equipment X revised from 5A to 7.5 A
Description of equipment X expanded.
Changes made at this Issue indicated by ‘revision bar’ in LH margin.
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2.
CONTENTS:
Title page
1. Summary of changes
2. Contents
3. Overview
4. Main Equipment Fitted
5. Rack Layout Schematic
6. Equipment List
7. Instrument Location, Function and Operation
8. Technical Requirements for Installation of Rack Mounted Equipment
9. Hazards
10. Scientific Equipment Approval – Conformity Statements
11. Failure Analysis
12. Gas Flow schematic
13. Power Distribution Box
14. Electrical Schematic Diagram(s)
15. Nominal Power Use summary table
16. Centre of Gravity Analysis
17. Summary of Attachments
Appendices
1.
2.
3.
4.
5.
6.
7.
8.
Operating Instructions
Emergency Shutdown Procedure
Actions to be taken in the event of a spill/leak/release of gas etc.
Aircraft Safety Information Card
COSHH Datasheets
Manufacturers datasheets
Electrical Cable Schedules
Scientific Equipment external to the Rack (Inlets etc)
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3.
OVERVIEW
General description of installation:
This instrument is designed to measure the night-time concentration of nitrate radical (NO3),
dinitrogen pentoxide (N2O5) and nitrogen dioxide (NO2) or nitrous acid (HONO) in the
atmosphere, using the technique of broad band cell enhanced absorption spectroscopy
(BBCEAS), as part of the forthcoming campaign ROle of Night time chemistry in controlling
the Oxidising Capacity of the AtmOsphere (RONOCO). The overall scientific objective can be
found in the Research Proposal for RONOCO.
Mention should be made to the purpose of the science & equipment and the campaign it is
primarily introduced into. List all abbreviations used.
CCN
CPC
FWVS
etc
etc
Cloud Condensation Nuclei
Condensation Particle Counter
Fluorescent Water Vapour Sensor
The XXX Rack will house a three-channel broad band cell enhanced absorption spectrometer. It
is self-contained and is to be calibrated pre-flight by two scientists from the front face of the
rack or the aisle of the aircraft.
Mention any inlets, other off-rack equipment (e.g. Pump Tray) and interfaces with other off-rack
equipment which might comprise the complete scientific equipment.
In-flight Operation:
Two scientists will be needed to tune the optical cells and to control and monitor the status of
the instruments from the front face of the rack or from the aisle.
Interface Connections:
The instrument requires connections with two inlets from the nearest window and with the
exhaust pipe of the aircraft.
A separate Pump Tray located adjacent to the rack provides an vacuum pump for the Inlet.
Refer to Appendices 1 and 2 for the basic Operating Instructions and Emergency Shutdown
procedures.
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4.
MAIN EQUIPMENT FITTED
3025 Condensation Particle Counter
3786 Condensation Particle Counter
Dual Column CCN Counter
FWVS Instrument
Qty 2 Vacuum Pumps
Qty 3 Compressed Gas Cylinders
Window blank mounted Inlet
Separate Pump Tray consisting of pump and controller
This is not an equipment list, only the main components and especially ‘stand alone’ vendor
supplied instruments need be listed.
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5.
Rack Layout Schematic
EXAMPLE (different from Equipment List)
13
20
18
14
17
19
7
1
8
3
Empty slot
4
9
5
10
6
11
12
2
Figure 1 Forward Rack Schematic
If components are installed in different ‘faces’ of the rack then additional alternative views may need to
be shown. N.B. Especially if the rack is assembled in a ‘3 shelf’ arrangement.
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6.
Equipment List
EXAMPLE (different from Rack Layout Schematic)
Item #
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
ID
CCN
CPS PC 1
CPS Pump
Grimm
5 3786 CPC
Power Box
LTI MFC1
LTI MFC2
Laptop
Vac. Pump
FWVS Box
Calib. box
NI Computer
Elec. Box
Full Name
DMT dual column CCN counter
Alicat pressure controller (CPS system)
KNF N86KNDC B 12V pump (CPS system)
Grimm Sky-OPC
Quant 3786 modified water filled ultra fine particle counter
CCN rack power distribution panel
Alicat Series 6 mass flow controller
Alicat Series 6 mass flow controller
Dell latitude D830 Series laptop and docking station
N86 KNE Vacuum pump for Grimm
Inlet box for FWVS system
FWVS calibration box
National Instrument computer for FWVS system control
FWVS electronics box
FWVS Screen
Sub Samplers
KVM Switch
Serial to USB
Keyboard and screen for FWVS NI computer
Grimm OPC sub samplers
CCN/FWVS KVM switch
Moxa 4:1 Serial to USB connector
The Item # should refer to the same item number shown in the rack layout schematic.
i.e. Item # 6 in the above table is the same item #6 identified in the rack layout schematic.
The Item #, ID and Full Name of equipment is the same used throughout the TSSE.
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7.
Instrument Location, Function and Operation
Equipment referred to in the following section corresponds to the Item # in Section 6.
7.1
Item # 1
CCN
The Dual Column CCN counter is manufactured by Droplet Measurement Technology and
operates on the principle that diffusion of heat in air is slower than diffusion of water vapor. The
column is mounted vertically with the ambient aerosol entering at the top, and the flow
progressively becomes supersaturated with water vapor as it traverses down the column. The
aerosol sample is laced at the center of the column where supersaturation is maximum; filtered
humidified sheath air surrounds the sample. The flow ratio is typically 1 part of sample to 10
parts of sheath air to ensure that the aerosol is exposed to a uniform supersatuation profile. The
vertical mounting, cylindrical geometry and a porous alumina bisque liner (which provides the
wetted surface down the column wall) minimize buoyancy effects and help droplets grow to
detectable size.
It is a self-contained unit occupied the entire RHS of the rack below the top shelf and operates
on a 28V dc supply.
7.2
Item # 2
CPS Pressure Controller
The CPS Pressure Controller is manufactured by Alicat Scientific and is mounted directly onto the top
shelf. It is connected between the Inlet pipe and the CPS Pump and operates on 12V dc supplied from the
Power Box (Item # 6).
7.3
Item # 3
CPS Pump
The CPS Pump is manufactured by KNF and is a model N86KNDC. It is mounted directly onto the top
shelf. In conjunction with the CPS Controller (Item # 2) it supplies a constant pressure flow to the CCN
(Item # 1). It also operates on 12V dc supplied from the Power Box (Item # 6).
The power box was supplied by the Aerodyne Research Inc. It is designed to take in 230V AC,
and convert to 24V DC before distributing the power to the other components. The box has been
modified to take in the standard power cable from the aircraft with a 6026-22-12-PN connector
at the back of the box. The 230 VAC is then taken out of the power distribution box and through
UPS 1 and then fed back into the power distribution box. From this the 230V AC is then
distributed through the original cabling and converted to 24V DC or is distributed to other
components in the rack.
7.4
Item # 4
Grimm Sky-OPC
The Grimm Series 1.129 Sky-OPC is a small light weight aerosol spectrometer which is fitted
directly onto the top shelf. Sample air is directly lead into the measurement chamber through the
aerosol air inlet. The airborne particles are measured inside the optical chamber by light
scattering. The scattering light pulse of every single particle is counted and the intensity of the
scattering light pulse classified to a certain particle size. The light source is a laser diode with a
wave length of 683nm and 40mW power. Optics focus the laser beam which illuminates a small
measurement volume evenly and consequently is lead into a light trap. Every particles´
scattering light is collected through a second optic using a scattering angle of 90° and is lead via
a mirror with an about 60° aperture angle focused on a detector diode. The detector signal will
be classified after amplification against the intensity into 1 of 31 size channels.
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• Interface: RS-232 Interface (USB or RS-232)
• Power supply: 24 VDC, external
The subsamplers (item # 16) attached to this rack are for use with the Grimm Sky-OPC. They
are used in conjunction with the nephelometer pumps to provide the variable flow rate at the
inlet for testing purposes.
The vacuum pump (item # 10) is also used with the Grimm Sky-OPC and is used to provide
vacuum for the sample to be drawn into the instrument.
7.5
Item #5 etc, etc
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8.
TECHNICAL REQUIREMENTS FOR THE INSTALLATION OF
RACK MOUNTED EQUIPMENT
8.1
General Design
The following table details the technical requirements and the corresponding qualifying
statement.
Technical Requirement
The equipment shall not have any features that
experience has shown to be hazardous. The
normal or abnormal functioning of this
equipment shall not adversely affect the
proper functioning of the aircraft systems and
should not otherwise adversely affect the
safety of the aeroplane or its occupants.
Materials used in its construction must be
appropriate to the intended function. Any
material the failure of which could lead to a
hazard to the aircraft or its occupants must
conform to a recognised specification and
must take into account the expected
environmental conditions.
Fasteners used must be appropriate to the
installation environment.
Fabrication methods shall be appropriate to
the expected service conditions.
Suitable protection of structure and
components should be made for the expected
environment.
The equipment should be of a kind and design
appropriate to its intended function and
labelled as to its identification, function and
limitations.
Each item of equipment should be marked to
allow its identification and to ensure its safe
operation. The marking should correspond
with the documentation for the equipment.
Where drainage of equipment is necessary,
means must be provided to achieve this
without spillage that could cause a hazard to
the aircraft.
Protrusion of items of equipment into the aisle
of the aircraft is not permitted where this
protrusion presents a snag or trip hazard to
occupants either moving about the cabin or
exiting the aircraft in an emergency. In
addition, any other protrusions should be
arranged to minimise possibility of injury to
occupants.
Qualifying Statement
The equipment does not have any features
that experience has shown to be hazardous.
The normal or abnormal functioning of this
equipment does not adversely affect the
proper functioning of the aircraft systems and
does not otherwise adversely affect the safety
of the aeroplane or its occupants.
Materials used in its construction are
appropriate for the intended function.
Fasteners used are appropriate to the
installation environment.
Fabrication methods meet expected service
conditions.
Suitable protection of structure and
components has been made for the expected
environment.
The equipment is of a kind and design
appropriate to its intended function and
labelled as to its identification, function and
limitations.
All components are identified by a unique
number shown in the Equipment List.
No liquids are used hence no drains are fitted.
Rack layout and fastenings of components are
designed to minimise risk of injury. Sharp
edges and protrusions have been removed.
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8.2
Structural Design
The following table details the technical requirements and the corresponding qualifying
statement.
Technical Requirement
The standard equipment racks are designed to
accommodate:
1.
A maximum equipped weight of 500lb
2.
Associated with this maximum weight,
a centre of gravity height no greater than 26in
from the floor, within 4in fore or aft and port
or starboard from the plan geometric centre of
the rack
3.
A maximum weight of any attached
equipped Rack Shelf of 150lb
Each item as part of the equipment that would
not be restrained by a casing must be
restrained under flight inertia loads defined by
BAE Systems Stress Dept. and conform to the
following emergency landing conditions:
Upward
3.0g
Forward
9.0g
Sideward
3.0g
Downward
6.0g
Rearward
1.5g
Qualifying Statement
1. The equipment rack maximum equipped
weight does not exceed 500lbs.
2. Centre of gravity analysis shows rack
weight distribution is within the permitted
parameters.
3. The maximum weight of any attached
equipped Rack Shelf does not exceed 150lbs.
Refer to Section 16 for the Centre of Gravity
Analysis.
All the attachment of items to the rack or
internal shelves is designed to restrain the
equipment under the required inertial loading.
This includes preventing the equipment from
shifting in a manner that could pose a hazard
to the aircraft or its occupants or nullify any of
the escape facilities. Refer to Section 17,
Summary of Attachments which gives details
of methods of fastening and any fastenings
used.
Equipment must be able to undergo the
negative accelerations described in the inertia
envelope without causing a hazard to the
aircraft or its occupants.
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8.3
Electrical
The following table details the technical requirements and the corresponding qualifying
statement.
Technical Requirement
Equipment should be suitably bonded to
protect from the effects of static, lightning and
electrical faults.
Any ElectroMagnetic Interference (EMI)
likely to be present in the equipment must not
result in hazardous effects upon the aeroplane
or its systems.
Qualifying Statement
Appropriate statement required.
The equipment does not present potentially
hazardous EMI to the aircraft systems. The
potential effect on flight instrumentation will
be conducted in an EMC test prior to flight.
The findings of that test will be reported
separately.
Battery installations must be appropriately Not applicable.
designed with consideration to appropriate
battery type
and
charging/discharging
safeguards. This includes any UPS systems.
Installations must ensure that the risk of All electrical components have been designed
electrical shock to occupants and servicing and installed so as to minimise the risk of
personnel is minimised.
electric shock to crew, occupants and servicing
personnel using normal precautions. Electrical
connections follow best practice to ensure
minimal risk of electric shock.
Wiring is to be Raychem type 55 (dual-walled Appropriate statement required.
airframe cable to Standard S3200) as far as
possible. Exceptions to this include limited
amounts of industrial type IEC power
connectors, and vendor supplied PVC
insulated interface cables (keyboard, mouse,
monitor, etc.
All wires and looms are to be adequately Appropriate statement required.
clipped and appropriately routed to protect
against mechanical damage. Non-latching
connectors (e.g. IEC mains plugs) are to be
clipped to adjacent cables or rack structure,
where possible, to minimise possibility of
shaking out of receptacle.
Exposed live contacts on any equipment is not
permitted.
Electrical components must be designed and Appropriate statement required.
installed so there is adequate physical
separation between it and other aeroplane
components and structure, and so that they are
protected from sharp edges and corners, in
order
to
minimise
potential
for
abrasion/chafing, vibration damage, and other
types of mechanical damage.
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Electrical components must be labelled or
otherwise identified using a consistent method
that facilitates identification of the component,
its function, and its design limitations, if any.
Labelling of cables, connectors, sockets,
lamps, switches, circuit breakers and fuses is
clear, permanent and indelible.
All cables are identified with unique marking
as shown in Appendix 7, Cable Schedule.
Automatic circuit protective devices must be Appropriate statement required.
used to minimise distress to the electrical
system and hazard to the aeroplane in the
event of wiring faults or serious malfunction of
the system or connected equipment.
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8.4
Mechanical/Fluid
The following table details the technical requirements and the corresponding qualifying
statement.
Technical Requirement
In each area of equipment where flammable
fluids or vapours might escape, there must be
means to minimise the possibility of ignition
of fluids or vapours and the resultant hazards if
ignition does occur. This may be shown by
analysis and should include means of detecting
leakage, flammability characteristics, possible
ignition sources and means for controlling or
extinguishing fire. Each area where flammable
fluids or vapours might escape by leakage
must be identified.
Any and all substances included within the
scientific instruments must be assessed and
must not constitute a hazard to the aircraft or
its occupants. This includes normal and
abnormal operation, and leakages. Appropriate
containment, detection and safety equipment
must be included to manage any potential
hazard.
High-energy rotors contained in equipment
must be able to withstand damage caused by
malfunctions, vibration, abnormal speeds and
abnormal temperature. Control devices must
ensure that operating limitations are not
exceeded in service. Any damage due to
failure of components must either be contained
within a casing or be shown to not adversely
affect the aircraft or endanger its occupants.
Compressed gas bottles
TBD
Qualifying Statement
Appropriate statement required.
Refer to Section 9 for list of potential hazards.
Refer to Appendix 3 for actions to be taken in
the event of a spill/leak.
Appropriate statement required.
Appropriate statement required.
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9.
HAZARDS
The following table lists potential sources which may constitute a hazard to the aircraft or its
occupants. It is by no means exhaustive and may be added to when appropriate.
Each individually identified hazard must have a corresponding statement. If it is not applicable
to this particular item of scientific equipment a ‘Not applicable’ statement must be made.
Refer to Appendix 5 for COSHH data sheets for each hazardous material.
Explosives
Flammable Liquids
Not applicable. No explosive devices fitted to
this rack.
5ppm NO in N2 high purity 2L @ 150 bar
Industrial grade oxygen 10 L @ 200 bar
Argon10L @ 200 bar
Not applicable.
Flammable Solids
Appropriate statement required.
Oxidizing Agents and Organic Peroxides
Appropriate statement required.
Toxic and Infectious Substances
Appropriate statement required.
Radioactive Substances
Corrosive Substances
Qty 2 Polonium 210 in-line ionisers each at
20mCi (740 MBq)
Appropriate statement required.
Cryogenic Chemicals
Appropriate statement required.
Permeation Sources
Appropriate statement required.
Liquid Chemicals
Appropriate statement required.
Solid Chemicals
Appropriate statement required.
Chemical Lamps
Appropriate statement required.
Lasers
Fully enclosed diode pumped frequency
doubled YAG laser, delivering 50mW power
at 532nm.
3kV supplied from QMS-100 to the
spectrometer.
Appropriate statement required.
Gases
High Voltage Sources
Batteries including Lithium-ion types and
UPS systems.
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10.
Scientific Equipment Approval – Conformity Statements
General
The rack and the equipment fitted therein are only required for scientific use. With the exception
of the flight intercom, rack mounted instruments are not directly connected to the flight systems.
The rack is not required for safe operation of the aircraft. Any failure of systems within or
connected to the rack are considered to be from the “no hazard to aircraft or occupants”
perspective.
The conformity notes refer to all items of equipment fitted on or connected to the rack unless a
particular element is specified.
Statements of Conformity
The behaviour of each item of scientific equipment under each of the environmental conditions
detailed below should be considered and assessed for possible hazard to the aircraft and
occupants.
Each individually identified category must have a corresponding statement. If it is not applicable
to this particular item of scientific equipment a ‘Not applicable’ statement or equivalent must be
made.
Category
Hazards
Conformity Statement
The overall design of the rack contains no feature inherently hazardous
to the aircraft or its occupants. Refer to Section 9 for list of Hazardous
materials fitted to this equipment, if applicable.
Flammable liquids 1. No flammable liquids are used in the rack. Refer to Section 9 for list of
Hazardous materials fitted to this equipment, if applicable.
Noise
No Excessive noise is emitted. Consider the external noise propagation.
Does the instrument have any holes, cavities etc which could cause
vibration and propagate a tone.
Electric Shock
All electrical components are designed to minimise the risk of electric
shock.
Burns
No component handled during normal operation is subject to a
temperature rise likely to cause injury.
Temperature and
No hazard is likely to arise from operation of the equipment as a result
pressure
of the changes in temperature and pressure within the normal flight
envelope.
Humidity
The equipment will not present a hazard as a result of changes in
humidity.
Shock & vibration
Failure of the installed equipment due to shock or vibration is not
considered to present a hazard to aircraft or occupants.
Vibration explosive It has been determined that there is negligible risk that the equipment
atmosphere
will cause an explosion of a flammable gas or vapour during flight
operations. Consider the effects of the equipment that may come into
contact with flammable fluids and vapours during normal and fault
conditions.
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Waterproofing
Fluid susceptibility
Sand and dust
High energy rotors
Fungus resistance
Salt spray resistance
Magnetic effect
Power input voltage
spikes
Emission of Radio
Frequency energy
Lightning direct
effects
Icing
Equipment does not need waterproofing as it is mounted above the floor
within the pressure cell. Also consider the effects of condensation and on
an externally mounted instrument, if applicable.
The installed equipment has no inherent susceptibility to aircraft fluids
such that would cause it to become a hazard.
Sand and dust ingress is not applicable as equipment is mounted above
the floor within the pressure cell. Consider the effects on an externally
mounted instrument, if applicable.
No hazards due to high-energy rotors are present. The pump motors are
considered to be of a negligible hazard.
Fungus resistance is not applicable as the installed equipment is mounted
above the floor within the pressure cell. Consider the effects on an
externally mounted instrument, if applicable.
Salt spray resistance is not applicable as the installed equipment is
mounted above the floor within the pressure cell. Consider the effects on
an externally mounted instrument, if applicable.
The installed equipment has no unusually high magnetic effects.
Failure of the installed equipment due to power input voltage spikes is
not considered to present a hazard to the aircraft or its occupants.
The installed equipment does not emit excessive undesired RF noise
which could cause interference with the aircraft systems. Refer to
Section 8.3
The equipment is internally mounted and is therefore not susceptible to
direct lightening effects. Consider the effects on an externally mounted
instrument, if applicable.
Icing is not applicable as equipment is mounted above the floor within
the pressure cell. Consider the effects on an externally mounted
instrument, if applicable.
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11.
Failure Analysis
For each item of equipment, known and foreseen modes of failure shall be identified with the
associated effect. Consideration should also be given to combinations of failures and
secondary effects. This exercise should include, but not be limited to the following:
The ‘Luminol’ reservoir is located within a
sealed containment enclosure of suitable
construction. Any spills can easily be
contained with this enclosure the capacity of
which is greater than the capacity of the
reservoir.
The ‘Luminol’ reservoir is filled at the
beginning of each flight and emptied at the end
of each flight by suitably trained personnel.
No high power lasers are present. Low power
lasers in CD-ROM drivers do not present any
hazard.
Failure to contain fluids
Failure to contain optical sources (lasers)
Failure of high energy rotating parts
Failure of components,
pipework under pressure
No high energy rotating parts are fitted. The
rack is limited to small equipment ventilation
fans, small pumps and CD-ROM drivers.
structure
and
All gas distribution components are suitable
for the pressure of the gas. This includes gas
cylinders, pipe/tube work, gas pressure
regulators, fittings and valves. All gas
tubes/pipes distributing pressurised gases and
fittings for connecting the tubes/pipes are
appropriate to the pressure of the gas.
Failure of cooling provisions
Appropriately placed temperature sensors shut
down instrument if excessive temperatures are
reached due to failure of the cooling.
Failure leading to creation of a heat source
Appropriate statement required.
Failure leading to creation of an ignition
source
No part of the installed equipment is inherently
prone to give rise to a hazardous ignition
source in the event of failure.
Failure of joints that are
disconnected between flights
Tube/pipe joints – these are not disconnected
during flights. Joints are tested when instrument is
initially fitted. Failure is unlikely to happen as
suitably approved connectors are used.
Failure of
connections
electrical
regularly
components
and
Electrical connections follow best practice.
Failure leading to creation of source of
electric shock
Appropriate statement required.
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12.
Gas Flow Schematic
Schematic of
DMT CCN/3025a CPC/3786 CPC pneumatic lines, also showing individual
components of CPS system.
Schematic of FWVS pneumatic system.
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13.
Power distribution box
Item
#
Designation
Voltage
Receptacle
Circuit
Breaker
SO 1
Input from SSP
ALL
6020-22-12-SN
N/A
SO 2
Lab 230V Input
230V
50HZ
6020-14-5-SN
N/A
SO 3
Not Used
SO 4
CPS
Current Current
230V
115V
Current
28V
ETA-5700-2A
12V dc
6020-8-98-SN
ETA-5700-1A
0.07A
Note 1
SO 5
CCN
28V dc
6020-8-98-SN
ETA-5700-20A
18A
SO 6
FWVS 28V
28V dc
6020-8-98-SN
ETA-5700-1A
0.43A
SO 7
FWVS 230V
230V
50HZ
6020-8-98-SN
ETA-5700-1A
1A
SO 8
Grimm SkyOPC
24V dc
6020-8-98-SN
ETA-5700-1A
0.14A
SO 9
Note 2
etc,etc
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Note 1
Note 2
The 12V dc supply is produced internally in the Power Distribution Box and is
derived from the 230V 50HZ input.
The 24V dc supply is produced internally in the Power Distribution Box and is
derived from the 230V 50HZ input.
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14.
Electrical Schematics
Electrical Schematic of Wet Neph/PSAP/Filters Rack
2
SSP
34
Filter
Pump soft
start unit
Rack power
distribution unit
Rack power
Master Switch
1
Filters
electronics unit
3
Cables
1. Refers to cable ID ARAMRF042001
2. Refers to cable ID ARAMRF042002
3. Refers to cable ID ARAMRF042003
4. Refers to cable ID ARAMRF042004
5. Refers to cable ID ARAMRF042005
6. Refers to cable ID ARAMRF042006
7. Refers to cable ID ARAMRF042007
8. Refers to cable ID ARAMRF042008
9. Refers to cable ID ARAMRF042009
10. Refers to cable ID ARAMRF042010
11. Refers to cable ID ARAMRF042011
12. Refers to cable ID ARAMRF042012
13. Refers to cable ID ARAMRF042013
14. Refers to cable ID ARAMRF042014
15. This cable is integral to the flowmeter PSU
16. This cable is integral to the hub PSU
17. Refers to cable ID ARAMRF042017
18. Refers to cable ID ARAMRF042018
19. Refers to cable ID ARAMRF042019
20. Refers to cable ID ARAMRF042020
21. This cable is integral to the laptop PSU
22. Refers to cable ID ARAMRF014004D
23. Refers to cable ID ARAMRF046002
24. This is a standard USB cable.
25. This is a standard 9 D female to 9 D male serial
communications cable.
26. This is a standard 9 D female to 9 D male serial
communications cable.
27. Refers to cable ID ARAMRF014003
28. Refers to cable ID ARAMRF013004
29. Refers to cable ID ARAMRF040003
30. This is a standard 9 D female to 9 D male serial
communications cable.
31. This cable is the same as ARAMRF046002
32. Refers to cable ID ARAMRF041056
33. This is a ribbon cable carrying comms between the
flowmeter and the laptop PC
34. Refers to cable ID ARAMRF041002 (standard power
umbilical.)
6
4
Filters
Filter
Pump
5
Flow meter 1
7
Flow meter 2
‘Wet’
Neph
Power Distribution
unit
10
Neph
PSU
8
25
9
‘Dry’
Neph
Wet Neph & PSAP
11
From
fore core
console
14
22
PSAP
12
PSAP
Control
19
Neph
pump
18
Flow meter
PSU
17
15
26
PSAP
Pump
13
Temp/humidity sensor
Temp sensor
Humidity sensor
Humidity sensor
Humidity sensor
Flow meter
& temp/
humidity
sensors
27
28
33
USB Hub
PSU
16
29
USB
Hub
24
Thermotek
heater/chiller
30
Laptop
& LAN
unit
Laptop
PSU
20
21
Laptop
PC
23
31
To aircraft
data hubs
Both ‘on-rack’ and ‘off-rack’ schematic diagrams should be displayed here, if applicable.
22
Rack
DLU
32
To aft core
console
UnivYork/GC-MS/Terpine/001
15.
Power use summary table
Item*
230 Vac
28 Vdc
24 Vdc
12 Vdc
5 Vdc
Nominal Power
3
1.8 A
50 W
4
2.9 A
80 W
5
10.8 A
6
7
0.13 A
54 W
6.7 A
120 W
3.3 A
43 W
10
0.174 A
40 W
11
0.065 A
15 W
12
0.52 A
120 W
13
3.75 A
900 W
14
0.75 A
18 W
15
0.75 A
18 W
17
1.0 A
24 W
18
0.35 A**
80 W
19
0.35 A**
80 W
Total
*
1642 W
Item numbering as listed in Section 6, Equipment List.
**
AC/DC adapters which are supplied with the laptops are used to convert the aircraft mains
power to 19.5 Vdc.
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16.
Centre of gravity analysis
The equipment fitted in the BBCEAS rack is made up of many items. Weights of these items were taken
by Dr. Jim Crawford at Cranfield on 18th, November, 2009.
Mass and height of each item in the BBCEAS rack
Item Number
Mass / kg
Height / m
1
6.1
1.135
6.924 On top plate
2
4.0
1.135
4.540 On top plate
3
4.0
1.135
4.540 On top plate
4
0.8
1.135
0.908 On top plate
5
10.8
0.786
8.489 RHS*
6
14.1
0.630
8.883 LHS
7
10.2
0.630
6.426 RHS
8
8.9
0.786
6.995 LHS
9
4.4
0.875
3.850 LHS
10
9.3
0.497
4.622 LHS
11
2.8
0.875
2.450 RHS
12
12.0
0.519
6.228 RHS
13
29.4
0.214
6.292 RHS
14
4.4
0.129
0.568 Bottom, LHS
15
4.4
0.129
0.568 LHS
16
20.0
0.155
3.100 Bottom, Both sides
17
1.5
0.341
0.512 LHS
18
6.5
0.919
5.974 LHS
19
6.5
0.919
5.974 RHS
20
1.3
0.390
0.507
Top aluminium plate
13.0
1.050
Bottom aluminium plate
11.0
0.066
Rack
34.6
0.495
Total
220.0
*
Moment / (kg m)
Notes
13.650 Top
0.726 Bottom
17.127 incl. fittings, tubes,
pipes, wires and
AV mounts
119.85
Left and right refer to view from the operation side.
The following calculations are based on the Centre of Gravity (COG) of each item being at the
geometric mid point.
COG of the BBCEAS rack is 119.85 kg m / 220.0 kg = 0.545 m (or 21.46”)
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UnivYork/GC-MS/Terpine/001
17.
XXX Rack – Summary of Attachments
Include sketches/ photographs to assist with explanation.
17.1
Bases of AV mounts for the top plate
Aluminium boards of thickness 10 mm were machined to appropriate sizes and are mounted to
the rack using 10 × ¼” screws (NSA, A102 17E) and self-locking nuts.
17.2
AV mounts for the top plate
Each of the six AV mounts (Paulstra, part number 7002 LA) is mounted to the above bases
using 4 × M5 countersunk stainless steel grade A2 screws (RS, part number 171-871) and selflocking nuts (RS, part number 521-939).
17.3
Top plate for optical cells
The aircraft-grade aluminium top plate with a thickness of 6 mm (Smiths Metal, AW6082T651) was machined to 42” × 24” and is mounted to the six AV mounts using 6 × M6
countersunk stainless steel grade A2 screws (RS part number 171-900).
17.4
Item 1, 2 & 3: optical cells for the measurements of NO3, NO2 and N2O5.
These three cells are mounted to the top plate using 20 × M6 cut-to-length (about 60 mm)
stainless steel grade A2 studs (RS, part number 280-391), nuts (RS, part number 527-274) and
locking washers. Two longer (about 80 mm) stainless steel grade A2 studs (RS, part number
280-391) were used for Cell 2 which at the bottom of the plate were fixed with nuts (RS, part
number 527-274) and locking washers and at the top of the plate were fixed with tapped
aluminium bars of diameter ½” whose threads were locked by loctite retainer. Two M6 stainless
steel grade A2 screws (RS, part number 293-397) are bolted into heli-coiled holes as it is
difficult to use the above-mentioned studs and nuts for these two positions.
17.5
Item 4: Preheating tube for the measurement of N2O5.
The preheating tube is held by two machined PTFE rings which are then fastened to two
aluminium supports. The supports are mounted to the top plate using 4 × M5 ZnPt steel screws
(RS, part number 560-108) and self-locking nuts (RS, part number 521-939).
17.6 Item 5, 6, 7, 8 & 9: Enclosure of spectrometers, LEDs, PMTs, power distribution units
and manifold purging units
All these five enclosures are 19” rack-mountable (Schroff, Multipac pro series) with heights
varying from 1U to 4U. The heights and depths of the enclosures are:
Spectrometer enclosure: 3U, 400 mm deep;
LED enclosure: 4U, 460 mm deep;
PMT enclosure: 4U, 460 mm deep;
Power distribution enclosure: 3U, 460 mm deep;
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UnivYork/GC-MS/Terpine/001
Manifold purging enclosure: 1U, 210 mm deep.
Each is mounted to commercial telescopic rails (RS, part number 261-7537) using 5 × M4
stainless steel grade A2 screws (RS, part number 527-050) and self-locking nuts (RS, part
number 767-810) on each side. The telescopic rails are fixed to the front and back mounting
strips of the rack using 4 × M6 stainless steel grade A2 countersunk screws (RS, part number
171-900) and self-locking nuts (RS, part number 521-945) in the front and 4 × M6 stainless steel
grade A4 screws (RS, part number 232-8293 or 232-8300) and self-locking nuts (RS, part
number 521-945) at the back.
17.7
Item 10, 11, 12: Lock-in amplifier, USB-serial adaptor and UPS
These three items were supplied with mounting brackets which allow them to be mounted to the
front mounting strip of the rack. For Item 10 and 12 which are about or over 9 kg, extra
reinforcement is provided by holding them using two aluminium bars of outer diameter of about
16 mm which are then mounted to the back mounting strip of the rack using 2 × M6 stainless
steel grade A4 screws (RS, part number 232-8293) for each item.
17.8
Bottom plate for pump, cylinder and mass flow controllers
The bottom aircraft-grade aluminium plate with a thickness of 6 mm (Smiths Metal, AW6082T651) is mounted to the rack using 4 × M6 stainless steel grade A2 countersunk screws (RS,
part number 171-900) and self-locking nuts (RS, part number 521-945). Moreover, 2 × M6 cutto-length stainless steel grade A2 studs (RS, part number 280-391) and self-locking nuts (RS,
part number 521-945) are used to attach the plate to the rack in the middle.
17.9
Item 13: Scroll pump
The scroll pump is mounted to the bottom plate using 4 × M8 stainless steel grade A2 screws
(RS, part number 290-152) and self-locking nuts (RS, part number 521-951).
17.10 Item 14 & 15: Mass flow controller 1 and 2
The two mass flow controllers have built-in mounting holes at the bottom which are used to
mount the controllers to the bottom plate using 7 (3 for Item 14 and 4 for Item 15) × 8-32 UNC
screws of length ¾”.
17.11 Item 16: Nitrogen cylinder
The nitrogen cylinder is held steady on top of the bottom plate, by two aluminium cylinder stops
(6” × 3” × 6 ¾”, thickness ¼”) in the front and at the back of it to prevent it from moving back
and forth and four cylinder clamps (Clampco, part number 94100-0725) to prevent it from
rolling around. Each cylinder stop is mounted to the bottom plate using 6 × M6 stainless steel
screws (RS, part number 290-146) and self-locking nuts (RS, part number 521-945), and each
cylinder clamp is mounted to the bottom plate using 2 × ¼” bolts and nuts which were provided
by the supplier Clampco.
17.12 Item 17: Fascia
The fascia is mounted to the rack mounting strip using 4 × M6 screws and self-locking nuts.
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UnivYork/GC-MS/Terpine/001
17.13 Item 18 & 19: Laptop computer 1 & 2
The two laptops, with one on each side of the rack, are held on top of two laptop trays (1.5 mm
thickness aluminium sheet) by aluminium brackets. The trays are mounted to the telescopic rails
(RS, part number 261-7537) using 4 × M4 ZnPt screws (RS, part number 560-861) and selflocking nuts (RS, part number 767-810) on each side of the tray. Each pair of the rails is then
mounted to the front and back mounting strips of the rack using 3 × M6 stainless steel grade A4
screws (RS, part number 232-8293) and 1 × M6 stainless steel grade A2 screws (RS, part
number 281-114).
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XXX Rack Appendices
1.
2.
3.
4.
5.
6.
7.
8.
Operating instructions (Normal)
Emergency shutdown procedure
Actions to be taken in the event of a spill/leak/release of gas etc.
Aircraft Safety Information Card
COSHH Datasheets
Manufacturers Datasheets
Electrical Cable schedules
Scientific Equipment external to the Rack (Inlets, Pump Tray etc)
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UnivYork/GC-MS/Terpine/001
Appendix 1
EXAMPLE
Preflight PERCA4 Standard Running Procedure
1 Determine when preflight power will be available. Minimum required for single operator – 4
hours, Minimum require for 2 operators - 3 hours
2 Before entering the aircraft prepare the 140 ml syringes with sufficient Luminol solution to
supply the detectors for preflight and flight time running
3 Prepare tray with syringes of luminol, nitrile gloves and blue roll for luminol fill procedure
4 Turn on personal CO monitor before entering aircraft and attach to person
5 Ensure that there is sufficient compressed air and zero Grade N2 present in the flight cylinders
~20 bar compressed air and ~42 bar zero grade N2
6 Turn on rack mounted CO monitor
7 Install the Linearisation unit(LIN unit)
8 Turn on electrical distribution box (EDB)
9 Turn on DC Supplies
10 Turn on power to LIN unit
11 Set 50 mlmin-1 flow rate to each of the 4 channels of the LIN unit
12 Disconnect lines to and from the Luminol reservoir ensuring the taps on the back of the
Isothermal unit (ISO unit) are in the off position.
13 Connect air vent from luminol reservoir to 2 l adapted Winchester bottle
14 Connect the Luer lock syringe fill line to the luminol supply line.
15 Connect Luer lock syringe to luminol supply line
16 Open tap to luminol air vent line
17 Open tap to luminol supply line
18 Open tap on Luer lock syringe
19 Inject Luminol solution into reservoir
20 Close Luer lock tap on syringe
21 Close tap to luminol supply line
22 Close tap to luminol air vent line
23 Disconnect Luer lock syringe and return to the transport tray
24 Repeat steps 15 through 23 for the required number of syringes of luminol
25 Reconnect luminol lines to and from reservoir
26 Turn on power to the ISO unit
27 Turn on power to PC and Inlets
28 Start current version of LUPOS software
29 Open taps to luminol supply and return lines
30 Turn on vacuum pump to supply vacuum to the luminol waste reservoir
31 Supply ~24psig to the luminol reservoir using on/off tap connected to the supply line
32 Make sure the poppet valve is not in use, if it is reduce regulator pressure on N2 supply
33 Use needle valves in the detector try to adjust luminol flow rate
34 Turn on power to the detectors
35 Supply high pressure compressed air to actuator
36 Open NO in N2 cylinder and CO Cylinder
37 Use current version of LUPOS to set parameters for inlet and sample flow rate control
38 Calibrate as required, connecting to external compressed air supply to conserve compressed
air in rack mounted cylinders for in flight use
End of Preflight
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UnivYork/GC-MS/Terpine/001
In Flight PERCA4 Running Procedure
In flight running of the PERCA is left to the discretion of the PERCA4 operator as no two
flights will require the same adjustments, however the following aircraft rules must be obeyed.
The PERCA4 operator must be seated for take off and landing

PERCA4 Running note - flow rate controls need to be set to hold to prevent the needle
valves from sticking when trying to compensate for the change in pressure during take
off and landing

If the PERCA4 is to be operated below x ft then the operator must wear a safety harness and
hard hat as directed by the in flight cabin crew.
The PERCA4 operator must remain connected to the PERCA4 rack at all times during flight
time below xx ft
End of in flight
Post flight PERCA4 Running Procedures
1 Determine how long science power will remain on for after the flight
2 Ask for an extension if post flight calibrations are needed ~1 hr 30 per inlet if NO2 and chain
length cals are needed
3 Use current version of LUPOS software to shut down gas supply to inlets – CO then NO in N2
and finally N2
4 Turn off Detectors
5 Turn off CO cylinder and NO in N2 cylinder
6 Turn off high pressure air supply to actuator
7 Turn off compressed air to luminol reservoir
8 Turn off vacuum pump provided the lines have been evacuated for 10 mins after closing the
CO cylinder
9 Close taps to luminol supply and return lines
10 Remove data from the PC using either memory stick or CD
11 Close down software and PC
12 Disconnect the luminol reservoir lines ensuring all tapes are closed first
13 Connect air vent from luminol reservoir to 2 l adapted Winchester bottle
14 Connect the Luer lock syringe fill line to the luminol supply line.
15 Connect the Luer lock syringe to the fill line
16 Open tap to the air vent line
17 Open the tap to the syringe fill line
18 Open Luer lock tap on syringe and remove luminol from reservoir
19 Close the Luer lock tap on the syringe
20 Close the tap on the syringe fill line
21 Close tap to the air vent line
22 Disconnect Luer lock syringe and return to transport tray
23 Repeat steps 15 through 22 are required
24 Disconnect the luminol Luer lock syringe fill line from the reservoir
25 Disconnect the air vent line from the reservoir
26 Reconnect the luminol reservoir line and ensure the taps are left in the close position
27 Disconnect the luminol waste reservoir lines ensuring the taps are in the off position
28 Connect air vent from luminol waste reservoir to 2 l adapted Winchester bottle
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UnivYork/GC-MS/Terpine/001
29 Connect the Luer lock syringe fill line to the luminol waste supply line.
30 Connect the Luer lock syringe to the fill line
31 Open tap to the air vent line
32 Open the tap to the syringe fill line
33 Open Luer lock tap on syringe and remove waste luminol from reservoir
34 Close the Luer lock tap on the syringe
35 Close the tap on the syringe fill line
36 Close tap to the air vent line
37 Disconnect Luer lock syringe and return to transport tray
38 Repeat steps 30 to 37 as required
39 Disconnect the luminol Luer lock syringe fill line from the waste reservoir
40 Disconnect the air vent line from the waste reservoir
41 Reconnect the luminol waste reservoir line and ensure the taps are left in the close position
42 Turn off rack mounter CO monitor
43 Turn off power to ISO unit, PC, Inlets DC supplies, LIN unit and EDB
44 Uninstall LIN unit and return to lab along with luminol fill tray
45 Turn off N2 cylinder making a note of all cylinder pressures on rack
46 Turn off personal CO monitor
End of post flight
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Appendix 2
EXAMPLE
Emergency PERCA4 Shut Down Procedure
1 Turn off CO cylinder
2 Turn off NO in N2, compressed air and N2 cylinders
3 Turn off power to the entire rack using main power switch on EDB
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Appendix 3
EXAMPLE
LUMINOL Solution
Refer to COSHH Datasheet.
Warning: Avoid contact with skin and eyes.
Wear suitable protective clothing and nitrile gloves.
Mop up with blue roll and wash area with cold water. Dispose of cleaning materials in sealed
plastic bag and dispose of in accordance with COSHH instructions.
In case of skin contact: Wash off with soap and plenty of water. Seek medical advice.
In case of eye contact: Rinse thoroughly with plenty of water for at least 15 minutes and seek
medical advice.
If swallowed: Never give anything by mouth to an unconscious person. Rinse mouth with plenty
of water and seek medical advice.
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Appendix 4
EXAMPLE
Aircraft Safety Information Card
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Appendix 5
EXAMPLE
Safety Data Sheet
Version : 1.02
Product : Nitrogen
MSDS Nr : 300-00-0033BOC(U)
Date : 31/07/2000
Replaces version dated : 02/08/1994
1 IDENTIFICATION OF THE SUBSTANCE/PREPARATION AND OF THE COMPANY
Product name Nitrogen
Chemical formula N2
Company identification see heading and/or footer
Emergency phone numbers see heading and/or footer
2 COMPOSITION/INFORMATION ON INGREDIENTS
Substance/Preparation Substance.
Components/Impurities Contains no other components or impurities which will influence the classification of the product.
CAS Nr 07727-37-9
EEC Nr (from EINECS) 231-783-9
3 HAZARDS IDENTIFICATION
Hazards identification Compressed gas
In high concentrations may cause asphyxiation.
4 FIRST AID MEASURES
Inhalation In high concentrations may cause asphyxiation. Symptoms may include loss of mobility/consciousness.
Victim may not be aware of asphyxiation.
Remove victim to uncontaminated area wearing self contained breathing apparatus. Keep victim warm
and rested. Call a doctor. Apply artificial respiration if breathing stopped.
5 FIRE FIGHTING MEASURES
Specific hazards Exposure to fire may cause containers to rupture/explode.
Non flammable
Hazardous combustion products None
Suitable extinguishing media All known extinguishants can be used.
Specific methods If possible, stop flow of product.
Move away from the container and cool with water from a protected position.
Special protective equipment for fire fighters Use self-contained breathing apparatus.
6 ACCIDENTAL RELEASE MEASURES
Personal precautions Evacuate area.
Wear self-contained breathing apparatus when entering area unless atmosphere is proved to be safe.
Ensure adequate air ventilation.
Environmental precautions Try to stop release.
Clean up methods Ventilate area.
7 HANDLING AND STORAGE
Handling and storage Suck back of water into the container must be prevented.
Do not allow backfeed into the container.
Use only properly specified equipment which is suitable for this product, its supply pressure and
temperature. Contact your gas supplier if in doubt.
Refer to supplier's container handling instructions.
Keep container below 50°C in a well ventilated place.
8 EXPOSURE CONTROLS/PERSONAL PROTECTION
Personal protection Ensure adequate ventilation.
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UnivYork/GC-MS/Terpine/001
9 PHYSICAL AND CHEMICAL PROPERTIES
Molecular weight 28
Melting point -210 °C
Boiling point -196 °C
Critical temperature -147 °C
Relative density, gas 0.97 (air=1)
Relative density, liquid Not applicable.
Vapour Pressure 20°C Not applicable.
Solubility mg/l water 20 mg/l
Appearance/Colour Colourless gas
Odour None
10 STABILITY AND REACTIVITY
Stability and reactivity Stable under normal conditions.
11 TOXICOLOGICAL INFORMATION
General No known toxicological effects from this product.
12 ECOLOGICAL INFORMATION
General No ecological damage caused by this product.
13 DISPOSAL CONSIDERATIONS
General To atmosphere in a well ventilated place.
Do not discharge into any place where its accumulation could be dangerous.
Contact supplier if guidance is required.
14 TRANSPORT INFORMATION
UN Nr 1066
Class/Div 2.2
ADR/RID Item Nr 2,1° A
ADR/RID Hazard Nr 20
Labelling ADR Label 2: non flammable non toxic gas
Other transport information Avoid transport on vehicles where the load space is not separated from the driver's compartment.
Ensure vehicle driver is aware of the potential hazards of the load and knows what to do in the event of
an accident or an emergency.
Before transporting product containers ensure that they are firmly secured and:
- cylinder valve is closed and not leaking
- valve outlet cap nut or plug (where provided) is correctly fitted
- valve protection device (where provided) is correctly fitted
- there is adequate ventilation.
- compliance with applicable regulations.
15 REGULATORY INFORMATION
Number in Annex I of Dir 67/548 Not included in Annex I.
EC Classification Not classified as dangerous substance.
Labelling of cylinders
-Symbols Label 2: non flammable non toxic gas
16 OTHER INFORMATION
Ensure all national/local regulations are observed.
Asphyxiant in high concentrations.
Keep container in well ventilated place.
Do not breathe the gas.
The hazard of asphyxiation is often overlooked and must be stressed during operator training.
Users of breathing apparatus must be trained.
Before using this product in any new process or experiment, a thorough material compatibility and safety study should be carried out.
Details given in this document are believed to be correct at the time of going to press. Whilst proper care has been taken in the preparation of this
document, no liability for injury or
damage resulting from its use can be accepted.
End of document.
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UnivYork/GC-MS/Terpine/001
Appendix 6
EXAMPLE
37
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Appendix 7
EXAMPLE
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UnivYork/GC-MS/Terpine/001
Appendix 8
EXAMPLE
CIMS Window Blank Inlet
The inlet consists of Swagelok 3/8 inch PFA Teflon tubing (p/n: PFA-T6-062-100). This tubing
is encased in a 3mm aluminium tube (6082 T6 Grade) on the inside of the aircraft and is encased
in a stainless steel tube in the window blank assembly which is directed outside the aircraft. The
aluminium tubing section is insulated with Kevlar as shown in figure 4, where the extra
durability and smoothness is needed for the stainless steel section, this section is insulated with
high temperature heatshrink (p/n: S1205-509). Heating of both the aluminium and stainless steel
tubes is achieved each using on Minco polyimide heater respectively (p/n: HK5263R559L12A).
The heaters are controlled using Love 32DZ P.I.D. controllers which are an integral component
of the Flow/Pressure/Valve control box, as detailed in section 2.3.3. The heaters are connected
via cables 6 and 7 using Amphinol (6020-8-98SN /6026-8-98PN) multipole connectors. A
thermal cut off switch is included to ensure that the temperature does not exceed 700C and a
certificate of compliance has been included.
The stainless steel section possesses a ½ inch outer diameter and forms a pressure seal with the
3/8 inch PFA tube via a bored through Swagelok ½ inch to 3/8 inch reducing union (p/n: SS810-6-6-BT), depicted in figure 4.
Air is sampled using a Picolino VTE3 (see section 2.2.1) at a flow rate of 40-60standard litres
per minute (SLM) and is measured using a 1579 300 SLM MKS flow meter (see section 2.2.2).
The sampled airflow enters the CIMS body via a TEQCOM M series 3 way PFA valve. The
PFA valve is attached to an aluminium mounting plate using two 8-32 bolts and the shelf is
attached to the CIMS rack using two M6 bolts. The valve is controlled by the
Flow/Pressure/Valve control box, as detailed in section 2.3.3. The valve is connected via cable 8
using MOLEX multipole connectors type connectors. The PFA valve enables air to be sampled
via the CIMS inlet (see Figure 1 below) or common aircraft inlet to measure the background of
the instrument.
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UnivYork/GC-MS/Terpine/001
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UnivYork/GC-MS/Terpine/001
Component: PFA valve
Manufacturer: TEQCOM
Supplier: TEQCOM
Documentation: Instruction Manual
Component: Love controller
Manufacturer: Dwyer Instruments
Supplier: University of Georgia Institute of Technology
Documentation: instruction Manual
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UnivYork/GC-MS/Terpine/001
Component: Scrubber Material
Manufacturer: Permapure
Supplier: Permapure
Documentation: manual
Material Safety Data Sheets
Component: MKS 1579 Mass flow Meter
Manufacturer: MKS Instruments
Supplier: MKS instruments
Documentation: Instruction Manual
Component: Picolino VTE3
Manufacturer: Thomas
Supplier: Thomas
Documentation: Instruction Manual
Certificate of Conformity
Component: Insulation
Manufacturer: Dupont
Supplier: Dale Intertec
Documentation: specifications
Component: Altech Hydro Purge
Manufacturer: Altech
Supplier: altech
Documentation: specifications
Component: Molex Multipole connector
Manufacturer: MoLex
Supplier: Farnell
Documentation: specifications
Component: Fittings for inlet
Manufacturer: Swagelok
Supplier: Swagelok
Documentation: specifications
Component: Bi-metallic NC thermostat,Open@70degC thermal switch
Manufacturer: RS Components
Supplier: RS Components
Documentation: Certificate of Compliance
Component: Fittings for inlet
Manufacturer: Swagelok
Supplier: Swagelok
Documentation: specifications
43