Space & Astronomy/Space and Astronomy (October 1993).iso/mac/TEXT/SHUTTLE/EQUIPMEN.TXT

Text File | 1993-02-06 | 50KB | 958 lines

"6_2_3_12_2.TXT" (14674 bytes) was created on 12-12-88

CREW EQUIPMENT

FOOD SYSTEM AND DINING

The middeck of the orbiter is equipped with facilities for food
stowage, preparation, and dining for each crew member.  The food
supply is categorized as either menu food or pantry food.  Menu food
consists of three daily meals per crew member and provides an average
energy intake of approximately 2,700 calories per crew member per day.
The pantry food is a two-day contingency food supply that also
contains food for snacks and beverages between meals and for
individual menu changes.  It provides an average energy intake of
2,100 calories per crew member per day.  The types of food include
fresh, thermostabilized, rehydratable, irradiated,
intermediate-moisture, and natural-form food and beverages.

If a payload is installed in the middeck in lieu of the galley, the
food preparation system is limited.  It consists of the water
dispenser, food warmer, food trays and food system accessories.

The water dispenser provides the flight crew with ambient and chilled
water for drinking and reconstituting food.  The water dispenser
consists of a housing assembly, rehydration station, hygiene water
quick disconnect and water lines.  Two flex lines 10 feet long connect
the housing assembly to the ambient and chilled potable water system.
Both lines have quick disconnects.  A 12-foot-long flex line with a
quick disconnect and water-dispensing valve supplies water for
personal hygiene.  The water selector valve amb position provides
ambient water to the rehydration station between 65 and 75 F.  The off
position prevents water from flowing to the rehydration station (it
does not shut off water flow to the personal hygiene water outlet
quick disconnect).  The chd water position provides chilled water to
the rehydration station between 45 and 55 F.

Depressing the hygiene water valve handle allows a constant flow of
ambient water.  Releasing the handle prevents water flow.  The
locked-open position allows a constant flow of ambient water without
holding the handle.

The rehydration station is an electronic dispensing system that
interfaces directly with food and beverage packages to provide
rehydration capability and drinking water for flight crew members.
The system dispenses 2, 3, 4 and 8 ounces of water through a
replaceable needle.  A spare needle is stowed at the rear of the
rehydration unit and another in the in-flight maintenance middeck
locker.  The needles are removed and installed with a 3/8-inch
open-end wrench.  Depressing the pwr push button at the rehydration
station provides power to the electronic rehydration system and an
indicating light is illuminated within the switch upon activation.
Depressing the pwr push button again deactivates the system.  The
water quantity rotary switch's 2, 3, 4 and 8 positions provide 2, 3, 4
and 8 ounces of water, respectively.  The needle must be inserted into
the package before depressing the fill push button to prevent free
water from being dispensed into the crew cabin environment.
Depressing the fill push button activates the electronic filling
mechanism when the water quantity selection has been made.  A light
comes on within the fill switch during filling and goes out when
filling is complete.  The operation is automatically deactivated.  The
bypass valve provides a continuous flow of water to the food
rehydration unit when the handle is depressed or lifted to the up
locked-open position.

The rehydratable food container is inserted into the rehydration
station, the water dispenser needle penetrates the rubber septum on
the rehydratable container, and the specified amount of water is
discharged into the container.  The rehydrated food is mixed and
heated, if required.  The rehydrated food container is opened by
grasping the center portion of the lid liner with the fingers,
piercing the liner with a knife or scissors and pulling the liner up
to aspirate air.  While grasping the center of the liner, the
astronaut swings container in a gentle forward and backward
semicircular motion to place food contents at the bottom of the
container.  The inside edge of the lid liner (three sides) is cut with
a knife or scissors to expose the food.

The rehydratable beverage container is inserted into the rehydration
station, the water dispenser needle penetrates the rubber septum on
the rehydratable container, and the specified amount of water is
discharged into the container.  The rehydratable beverage is mixed and
heated, if required.  A plastic clip is affixed to the straw in the
closed position, the probe end of the straw is inserted into the
container rubber septum, the straw is placed in the mouth, the clip is
released, and the beverage is drunk.  All straws are color-coded for
each crew member.

Food trays are kept in a middeck stowage locker (or in the galley, if
installed) at launch and are removed and installed in the use
locations during preparations for the first meal.  The tray is a
clear, anodized aluminum sheet that restrains food and accessories
during dining.  The trays are color-coded for each crew member.
Velcro on the bottom of the food trays allows them to be attached to
the front of the middeck lockers (or the galley door, if installed)
for food preparation or dining.  The straps will also hold the trays
on the crew member's leg for dining.  A cutout on the tray allows
three rehydratable food packages to be secured to the tray.  Another
cutout with rubber strips adapts to various-sized food packages,
including cans, pouches and rehydratable food packages.  Two magnetic
strips hold eating utensils and two 0.75-inch-wide binder clips on the
tray retain such things as condiment packets and wipes.  Accessories
used during food preparation and dining include condiments, gum and
candy, vitamins, wet wipes, dry wipes, drinking containers, drinking
straws, utensils and a re-entry kit that contains salt tablets and
long straws.

Condiments include salt, pepper, taco sauce, hot pepper sauce, catsup,
mayonnaise and mustard.  The salt and pepper are liquids stored in
small plastic squeeze bottles.  The remaining condiments are packaged
in individual, sealed, flexible plastic pouches.  Vitamin tablets
supplement dietary requirements.  Wet wipes are packaged in 21
individual packets per dispenser for cleaning utensils after dining.
A light spring action retains and positions wipes for dispensing.
Empty beverage containers of rigid plastic for drinking and storing
water are carried in crew members' clothing and can be filled at the
water dispenser.  Approximately five to 10 different color-coded
straws are provided for each crew member (depending on the flight's
duration) for drinking beverages and water.  Additional straws are
kept in the pantry beverages and various menu locker trays.
Color-coded utensils include a knife, two spoons (large and small), a
fork and a can opener for each crew member.  They are stowed with a
soft plastic holder that has a Velcro snap cover.  Dry wipes are
packaged in a 30-wipe container that can be attached to the crew cabin
wall with Velcro for cleanup after dining.  The re-entry kit consists
of one package containing eight salt tablets for each crew member and
long straws (four per crew member).  Two salt tablets are to be taken
with 8 ounces of water or other beverage by each crew member four
times before entry.  The re-entry kit may be stowed in one of three
locations depending on space available-with the accessories, near the
last meal to be consumed on orbit or with the pantry beverages.

The food warmer is a portable heating unit that can warm a meal for at
least four crew members within one hour when the galley is not flown.
It is stowed in a middeck locker at launch and is removed and
installed during meal preparation activity.  The food is heated by
thermal conduction on a hot plate (element).  The warmer is
thermostatically controlled between 165 and 175 F.  The case is
constructed of aluminum with an exterior envelope of 13 by 18 by 6
inches.  It has latches and is lined with clear urethane foam
insulation coated with room-temperature vulcanizing compound.  The
case has straps for handling and on-orbit installation.  The exterior
contains controls and displays, a power connector that interfaces with
the power cable and Velcro attachment.  A hinged element is sandwiched
between two aluminum plates and is contained by a fiberglass frame.
The aluminum plates have spring-bungee restraints for foil-backed food
packages on one side.  An on/off switch provides two-phase ac power to
the unit and a light indicates the warmer is operating.  The power
cable is 156 inches long and attaches to a middeck ac utility outlet.
The cable is stowed inside the case at launch.

A maximum of 14 packages can be installed on the side of the spring
bungees and eight on the other side.  Rehydratable beverages should be
placed on the side opposite the spring bungees, and the foam on the
other side is additionally relieved to prevent the packages from
popping out in zero gravity.  When 14 rehydratable packages are
heated, no foil-backed food pouches can be heated.  A maximum of six
foil-backed food pouches can be heated in conjunction with 12
rehydratable packages.  When foil-backed pouches are heated, only four
rehydratable packages can be heated on the side of the spring bungees.
The foil-backed pouches are stacked three deep.  Four rehydratable
packages are inserted in the outer recessed foam cutouts.  At the
bottom of the cutouts, 0.5-inch-thick uncoated foam absorbs moisture
or spilled liquids.

The galley is a multipurpose facility that provides a centralized
location for one individual to handle all food preparation activities
for a meal.  The galley has facilities for heating food, rehydrating
food and stowing food system accessories and food trays.  The galley
consists of a rehydration station, oven, food trays and food system
accessories.

The oven is divided into two principal compartments-a lower
compartment designed for heating at least 14 rehydratable food
containers inserted on tracks and an upper compartment designed to
accept a variety of food packages, including the rehydratable
containers.  At least seven food pouches can be heated in the upper
compartment and are held against the heat sink by four spring-loaded
plates.  The oven has a heating range of 145 to 185 F.  During launch
and entry, the oven door is held closed by a restraining strap, which
is removed from the door by releasing the snap for on-orbit
operations.  An on/off switch enables and removes power to three fans.

The rehydration station dispensing system interfaces directly with
food and beverage packages, providing rehydration capability and
drinking water for crew members.  A gauge indicates hot water
temperatures of 100 to 220 F.  The volume/ounces switch selects the
volume of water to be dispensed by the rehydration station in
0.5-ounce increments from 0.5 of an ounce to 8 ounces.  The yellow hot
push button indicator allows hot water to be dispensed when it is
depressed and is illuminated when energized.  When the selected volume
of water has been dispensed, the push button will begin to flash on
and off.  The light will be extinguished when the food package is
retracted, releasing the hydration station lever arm/limit switch.
The rehydration station lever arm/limit switch serves as an interlock
so water can be dispensed only when a food package is connected to the
needle.  The food package makes contact with the rehydration station
lever, which activates the limit switch (note that the flight crew
does not physically actuate the lever).  The blue cold push button
indicator allows cold water to be dispensed when it is depressed and
is illuminated when energized.  When the selected volume of water has
been dispensed, the push button will begin to flash on and off.  The
light will be extinguished when the food package is retracted,
releasing the rehydration station lever arm/limit switch.

The galley light is located on the upper left-hand side of the galley
structure surface and has a single light brightness control.  Moving
the knob clockwise from off applies power to the light and provides
variable brightness control.

Two condiment dispensers are attached to the galley by Velcro tabs on
the back of the dispensers.  The dispensers are available for holding
individual packets, such as catsup, taco sauce, mayonnaise and
mustard, on the front panel below the oven.  The dispensers are
open-ended boxes designed to hold the stack of packets together so
they may be individually removed as needed.  A slide plate keeps the
packets from becoming loose as the items are depleted.

A single dispenser for holding individual packets of wet wipes is
located on the front panel below the oven and is slightly different in
design than the condiment dispensers.

Dispensers for liquid salt and pepper and vitamins can be restrained
by clips conveniently located below the rehydration station.

Food trays and food system accessories are the same as those used on
flights without the galley.

On the upper left-hand corner of the galley behind a Teflon cloth
panel is an MV3 valve that has emer off and on positions.  The on
position serves as the nominal open position of the manual shutoff
valve, and emer off serves as a manual shutoff valve for the ambient
temperature water supply to the galley.

On the upper right-hand corner of the galley behind a Teflon cloth
panel are test connectors, a dc power bus A and B switch and a flush
port quick-disconnect test port.  The two test connectors serve as a
hookup for ground support equipment.  The dc power bus A switch's on
position activates the galley oven heaters, rehydration station system
and one of six water tank strip heaters; the off position deactivates
the heaters.  The dc power bus B switch's on position activates five
of the six galley water tank strip heaters, and the off position
deactivates them.  The flush port quick disconnect serves as the
galley water system GSE flush port.

On the lower left-hand side of the galley is an auxiliary port water
quick disconnect that allows the crew members to obtain ambient
potable water when the MV3 valve is off or hygiene water when the
12-foot flex line and water dispensing valve are attached to the quick
disconnect.

Three one-hour meal periods are scheduled for each day of the mission.
This hour includes actual eating time and the time required to clean
up.  Breakfast, lunch and dinner are scheduled as close to the usual
hours as possible.  Dinner is scheduled at least two to three hours
before crew members begin preparations for their sleep period.


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SHUTTLE ORBITER MEDICAL SYSTEM

The shuttle orbiter medical system is required to provide medical care
in flight for minor illnesses and injuries.  It also provides support
for stabilizing severely injured or ill crew members until they are
returned to Earth.  The SOMS consists of two separate packages: the
medications and bandage kit and the emergency medical kit.  The MBK is
blue and the EMK is also blue with red Velcro.

The medical kits are stowed in a modular locker in the middeck of the
crew compartment.  If the kits are required on orbit, they are
unstowed and installed on the locker doors with Velcro.

Each kit contains pallets.  The MBK pallet designators are D, E and F.
The D pallet contains oral medications consisting of pills, capsules
and suppositories.  The E pallet contains bandage materials for
covering or immobilizing body parts.  The F pallet contains
medications to be administered by topical application.

The EMK pallet designators are A, B, C and G.  The A pallet contains
medications to be administered by injection.  The B pallet contains
items for performing minor surgeries.  The C pallet contains
diagnostic/therapeutic items consisting of instruments for measuring
and inspecting the body.  The G pallet contains a microbiological test
kit for testing for bacterial infections.

The diagnostic equipment on board and information from the flight crew
will allow diagnosis and treatment of injuries and illnesses through
consultation with flight surgeons in the Mission Control Center in
Houston.


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OPERATIONAL BIOINSTRUMENTATION SYSTEM

The operational bioinstrumentation system provides an amplified
electrocardiograph analog signal from either of two designated flight
crew members to the orbiter avionics system, where it is converted to
digital tape and transmitted to the ground in real time or stored on
tape for dump at a later time.  The designated flight crew members
wear the OBS during the ascent and entry phases.  On-orbit use will be
limited to contingency situations.

The OBS electrodes are attached to the skin with electrode paste to
establish electrical contact.  The electrode is composed of a plastic
housing containing a non-polarizable pressed pellet.  The housing is
attached to the skin with double-sided adhesive tape and the pellet
contacts the skin.  There are three electrodes on the harness marked
LC (lower chest), UC (upper chest) and G (ground).

The ECG signal conditioner is a hybrid microcircuit with variable gain
(adjusted for each crew member before flight).  It provides a zero- to
5-volt output and has an on/off switch within the input plug, which is
actuated when the intravehicular activity biomed cable is plugged in.
The unit has batteries that will not be replaced in flight.

The IVA biomed cable connects to the signal conditioner and is routed
under the IVA clothing to connect to the biomed seat cable.  The
biomed seat cable is routed to one of the biomed input connectors
located on panel A11, A15 or M062M.  Rotary control switches on panel
R10 provide circuits from the biomed outlets to the orbiter's network
signal processor for downlink or recording.  The two rotary switches
on panel R10 are biomed chan nel 1 and channel 2 .  Extravehicular
activity positions provide circuits for the EVA UHF transceiver.

The electrode application kit contains components to aid in the
application of electrodes.  The components include wet wipes,
double-sided adhesive tape, overtapes, electrode paste and a cue card
illustrating electrode placement.


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RADIATION EQUIPMENT

The harmful biological effects of radiation must be minimized through
mission planning based on calculated predictions and monitoring of
dosage exposures.  Preflight requirements include a projection of
mission radiation dosage, an assessment of the probability of solar
flares during the mission and a radiation exposure history of flight
crew members.  In-flight requirements include the carrying of passive
dosimeters by the flight crew members and, in the event of solar
flares or other radiation contingencies, the readout and reporting of
the active dosimeters.

There are four types of active dosimeters: pocket dosimeter high,
pocket dosimeter low, pocket dosimeter FEMA and high-rate dosimeter.
All four function in the same manner and contain a quartz fiber
positioned to zero by electrostatic charging before flight.  The unit
discharges according to the amount of radiation received; and as the
unit discharges, the quartz moves.  The position of the fiber along a
scale is noted visually.  The PDH unit's range is zero to 100 rads.
The PDF and PDL units' ranges are zero to 200 millirads and the HRD
unit's range is zero to 600 rads.

The rad is a unit based on the amount of energy absorbed and is
defined as any type of radiation that is deposited in the absorbing
media, and radiation absorbed by man is expressed in roentgen
equivalent in man, or rems.  The rem is determined by multiplying rads
times a qualifying factor that is a variable depending on wavelength,
source, etc.  For low-inclination orbits (35 degrees and lower), the
qualifying factor is approximately equal to one; therefore, the rem is
approximately equal to the rad.  In space transportation system
flights, the doses received have ranged from 0.05 to 0.07 rem, well
below flight crew exposure limits.

The flight crew's passive dosimeters are squares of fine-ground photo
film sandwiched between plastic separators in a light-proof package.
Radiation striking the silver halide causes spots on the film, which
can be analyzed after the flight.  Included in the badge dosimeters
are thermoluminescent dosimeter chips, which are analyzed on Earth.

Passive radiation dosimeters are placed in the crew compartment before
launch by ground support personnel and removed after landing for
laboratory analysis.  Each flight crew member carries a passive
dosimeter at all times during the mission.  The remaining dosimeters
are stowed in a pouch in a middeck modular locker.  If a radiation
contingency arises, the PDL, PDH, HRD and PDF active dosimeters will
be unstowed, read, and recorded for downlink to the ground.


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CREW APPAREL

During launch and entry, crew members wear the crew altitude
protection system, which consists of a helmet; communications cap;
pressure garment; anti-exposure, anti-gravity suit; gloves; and boots.

The crew wears escape equipment over the CAPS during launch and entry.
It consists of an emergency oxygen system; parachute harness,
parachute pack with automatic opener, pilot chute, drogue chute and
main canopy; a life raft; 2 liters of emergency drinking water;
flotation devices; and survival vest pockets containing a
radio/beacon, signal mirror, shroud cutter, pen gun flare kit, sea dye
marker, smoke flare and beacon.  Manual activation of the parachute
automatic opening sequences is provided, as well as manual release of
the parachute main canopy.

On orbit, optional clothing and equipment include underwear, urine
collection devices, eyeglasses, communications headset, emesis bag,
flashlight, Swiss army knife, kneeboard, pens and pencils, stowage
bags, watches and food and drink containers.

Crew clothing and equipment used during on-orbit activities include
flight suits, IVA trousers, IVA jackets, IVA shirts, sleep shorts, IVA
soft slippers, underwear, scissors/lanyard, pocket dosimeter and
pocket food.

Crew clothing is designed for use by 90 percent of the male and female
population, the 5th to 95th percentile.


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SLEEPING PROVISIONS

Sleeping provisions for flight crew members consist of sleeping bags,
sleep restraints or rigid sleep stations.  The sleeping arrangements
can consist of a mix of bags and sleep restraints or rigid sleep
stations on a given mission.  During a mission with one shift, all
crew members sleep simultaneously.  If all crew members sleep
simultaneously, at least one crew member will wear a communication
headset to ensure reception of ground calls and orbiter caution and
warning alarms.

If sleeping bags are used, they are installed on the starboard middeck
wall and deployed for use on orbit.

If the rigid sleep station is used on a mission, it is installed on
the starboard side of the middeck.  There are two types of rigid sleep
stations.  One sleep station type accommodates three crew members and
the other accommodates four.

If the rigid sleep station is not installed for a mission, a sleeping
bag is furnished each crew member.  Each sleeping bag contains a
support pad with adjustable restraining straps and a
reversible/removable pillow and head restraint.  Apollo sleeping bags
may be provided for the crew members on request.  The Apollo sleeping
bag is constructed of beta material and is perforated for thermal
comfort.

Six adjustable straps permit the sleeping bag to be adjusted to its
proper configuration.  Three helical springs above the adjustable
straps on one side of the bay relieve loads exerted by the crew member
on the crew compartment structure.  Six pip pins allow the bag to be
attached to the middeck locker face in either a horizontal or vertical
configuration.  Two elastic adjustable straps restrain the upper and
lower parts of the body in the bag.  Velcro strips on the ends of both
sides of the head restraint attach it to the pillow.  A double zipper
arrangement permits the sleeping bag to be opened and closed from the
bottom to the top of the bag.  One zipper on each side of the sleeping
bag allows the bag to be attached to a support pad for better
rigidity.

The Apollo beta cloth sleeping bag has four adjustable straps with pip
pins that are connected to any two lockers in the middeck separated by
a distance equal to a four-tiered locker configuration.  For torso
restraint, a single two-piece strap is provided and a single zipper
opens the bag.  The bags are stowed in a middeck locker during launch
and entry.

A sleep kit is provided for each crew member and is stowed in the crew
member's clothing locker during launch and entry.  Each kit contains
eye covers and ear plugs for use as required during the sleep period.

The three- or four-tier rigid sleep stations contain a sleeping bag,
personal stowage provisions, a light and a ventilation inlet and
outlet in each of the tiers.  The cotton sleeping bag is installed on
the ground in each tier and held in place by six spring clips.  The
light in each tier is a single fluorescent fixture with a brightness
control knob and an off position.  The air ventilation inlet duct is
an air diffuser similar to an automobile ventilation duct.  It is
adjusted by moving the vane control knob.  The air ventilation outlet
duct is located in the fixed panel at each tier and is opened or
closed by moving the vane control knob.  The air inlet is located at
the crew member's head.  The outlet is at the feet.  All crew members'
heads are toward the airlock and their feet toward the avionics bay.

In the three-tier configuration, the upper and middle crew members
face the ceiling and the lower tier crew member faces the floor.  The
fixed panel at the lower sleep station is removable to provide access
to the cabin debris trap door for cleaning the cabin filter, to gain
access to floor locker MD76C and to enter the forward portion of the
lower equipment bay to clean the avionics bay fan filter.

In the four-tier configuration, the bottom tier sleep restraint hookup
provision allows the crew member to position himself at a 15-degree
angle, which provides more room, or in the normal horizontal position.
The sleeping bag, personal stowage provisions, light and ventilation
inlet and outlet are the same as in the three-tier configuration.  The
head and feet orientations of the crew members are also the same as in
the three-tier configuration.  The lowest tier is removable so access
can be obtained to the cabin debris trap door to clean the cabin
filter, gain access to floor locker MD76C and enter the forward
portion of the lower equipment bay to clean the avionics bay fan
filter.

The three-tier rigid sleep station is made of plastic honeycomb panel
and weighs approximately 205 pounds.  The four-tier rigid sleep
station is made of metal and weighs 173 pounds.

A 24-hour period is normally divided into an eight-hour sleep period
and a 16-hour wake period for each crew member.  Forty-five minutes
are allocated for the crew members to prepare for the sleep period and
another 45 minutes when they awake to wash and get ready for the day.
Enter an option number, 'G' for GO TO, ? for HELP, or


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PERSONAL HYGIENE PROVISIONS

To maintain good hygiene and appearance, personal hygiene and grooming
provisions are furnished for both male and female flight crew members.
Water is provided by the water dispensing system.

A personal hygiene kit is furnished each crew member for brushing
teeth, hair care, shaving, nail care, etc. A kit is also furnished
with articles essential to female hygiene and grooming.

Two washcloths and one towel per crew member per day are provided in
addition to two paper tissue dispensers per crew member for each seven
days.  The washcloths are 12 by 12 inches and the towels 16 by 27
inches.  The tissues are absorbent, multi-ply, low-linting paper.
Rubber restraints with a Velcro base allow the crew members to
restrain their towels and washcloths on the waste management door or
middeck walls.

The personal hygiene provisions are stowed in middeck stowage lockers
at launch and are removed for use on orbit.


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HOUSEKEEPING

In addition to time scheduled for sleep periods and meals, each crew
member has housekeeping tasks that require from five to 15 minutes of
his time at intervals throughout the day.  These include cleaning the
waste management compartment, the dining area and equipment, floors
and walls (as required), the cabin air filters; trash collection and
disposal; and changeout of the crew compartment carbon dioxide
(lithium hydroxide) absorber canisters.

The materials and equipment available for cleaning operations are
biocidal cleanser, disposable gloves, general-purpose wipes and a
vacuum cleaner.  The cleaning materials and vacuum are stowed in
middeck lockers.  The vacuum cleaner is powered by the orbiter's
electrical power system.

The biocidal cleanser is a liquid detergent formulation in a container
approximately 2 inches in diameter and 6 inches long.  The container
has a built-in bladder, dispensing valve and nozzle.  The cleanser is
sprayed on the surface to be cleaned and wiped off with dry
general-purpose wipes.  It is used for periodic cleansing of the waste
collection system urinal and seat and the dining area and equipment.
It is also used, as required, to clean walls and floors.  Disposable
plastic gloves are worn while using the biocidal cleanser.

General-purpose wipes are also used for general-purpose cleaning.

The vacuum cleaner is provided for general housekeeping and cleaning
of the crew compartment air filters and Spacelab fil ters (on Spacelab
missions).  It has a normal hose, extension hose and several
attachments.  It is powered by the orbiter dc electrical power system.

Trash management operations include routine stowage and daily
collection of wet and dry trash, such as expended wipes, tissues and
food containers.  Wet trash includes all items that could offgas.  The
equipment available for trash management includes trash bags, trash
bag liners, wet trash containers and the stowable wet trash vent hose.

Three trash bags are located in the crew compartment.  Each bag
contains a disposable trash bag liner.  Two bags are designated for
dry trash and one for wet trash.  At a scheduled time each day, the
trash bag liner for dry trash is removed from its trash bag.  The
liner is closed with a strip of Velcro and stowed in an empty locker.

When more than 8 cubic feet of wet trash is expected, the trash bag
liners for wet trash are removed at a scheduled time each day and
placed in a wet trash container.  The container is then closed with a
zipper and the unit is stowed.  If expansion due to offgassing is
evident, the container is connected to a vent in the waste management
system for overboard venting of the gas.

The wet trash container is made of airtight fabric and is closed with
a seal-type slide fastener.  The container has a volume of
approximately 0.7 cubic foot and has an air inlet valve on one end and
a quick disconnect on the other end.  It is attached to the waste
management vent system beneath the commode, enabling air to flow
through the wet trash container and then overboard.  It is attached
through a 41-inch- long vent hose filter.  When the container is full,
it is removed and stowed in a modular locker.

An 8-cubic-foot wet trash stowage compartment is available under the
middeck floor.  Each day, the trash bag liners for wet trash are
removed from the trash bags and stowed in the wet trash stowage
compartment, which is vented overboard.  If the compartment becomes
full, the trash bag liners for wet trash are stowed in wet trash
containers.


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SIGHTING AIDS

Sighting aids include all items used to aid the flight crew within and
outside the crew compartment.  The sighting aids include the crewman
optical alignment sight, binoculars, adjustable mirrors, spotlights
and eyeglasses.

The COAS is a collimator device similar to an aircraft gunsight.  Two
are installed in the crew compartment flight deck.  One COAS is
mounted during launch and entry over the positive X commander's
forward window and on orbit is removed and mounted next to the aft
flight deck overhead right negative Z window.  The other COAS is
mounted at the aft flight deck station for checking the alignment of
the payload bay doors.

When the COAS is mounted at the commander's station, it allows the
viewers to reassure themselves of proper attitude orientation during
the ascent and deorbit thrusting periods.  When the COAS is removed
from the commander's station to the aft flight deck for on-orbit
operations, it provides a backup to the orbiter star trackers for
inertial measurement unit alignment.  It is also used as the primary
optical instrument for measuring range and rotational rates and allows
the flight crew members to align the vehicles and dock.

The COAS consists of a lamp with an intensity control, a reticle, a
barrel-shaped housing, a mount, a combiner assembly and a power cable.
The reticle consists of a 10-degree circle, vertical and horizontal
cross hairs with 1-degree marks, and an elevation scale on the right
side of minus 10 degrees to 31.5 degrees.

For IMU alignments, the flight crew member at the aft flight deck
station maneuvers the orbiter using the COAS at the right overhead
negative Z window until the selected star is in the field of view.
The crew member continues maneuvering the orbiter until the star
crosses the center of the reticle.  At the instant of crossing, the
crew member makes a mark, which means he depresses the att ref
(attitude reference) push button.  At the time of the mark, software
stores the gimbal angles of the three IMUs.  The mark can be taken
again if it is felt the star was not centered as well as it could have
been.  When the crew member feels a good mark was taken, the software
is notified to accept it.  Good marks for two stars are required for
an IMU alignment.

By knowing the star being sighted and the COAS location and mounting
relationship in the orbiter, software can determine a line-of-sight
vector from the COAS to the star in an inertial coordinate system.
Line-of-sight vectors to two stars define the attitude of the orbiter
in inertial space.  This attitude can be compared to the attitude
defined by the IMUs, and if the IMUs are in error, they can be
realigned to the more correct orientation by the COAS sightings.

The COAS requires 115-volt ac power for reticle illumination.  The
COAS is 9.5 by 6 by 4.3 inches and weighs 2.5 pounds.

The 10-by-40 binoculars are a space-modified version of the commercial
Leitz Trinovid binocular noted especially for its small size, high
magnification, wide field of view, and rugged sealed construction.
The 7-by-35 binoculars are noted for close focal distance at high
magnification.  The 14-by-40 gyrostabilized binoculars contain a
gyrostabilized system that enhances target acquisition and retention.
When the crew member is subjected to ambient vibrations or hand tremor
while using the gyrostabilized binoculars, the target image remains
clear and stable.  The gyrostabilized binoculars are electrically
powered by six alkaline-type AA batteries and will operate
continuously up to three hours on one battery pack.

Adjustable mirrors are installed before launch on handholds located
between windows 2 and 3 for the commander and windows 4 and 5 for the
pilot.  During ascent and entry, the commander and pilot use the
adjustable mirrors to better see controls that are in obscured areas
of their vision.  On orbit, the mirrors can be removed and stowed if
desired.  Each mirror is approximately 3 by 5 inches and weighs
approximately 1 pound.

The spotlight is a high-intensity, hand-held flashlight powered by a
battery pack consisting of five 1.2-volt one-half D size
nickel-cadmium batteries.  The spotlight produces a 20,000-candlepower
output with a continuous running time of 1.5 hours.  The lamp is a
6-volt tungsten filament and cannot be replaced in flight.  A spare
battery pack is available on board.

For those crew members requiring them, two pairs of eyeglasses are
available on board.


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MICROCASSETTE RECORDER

The microcassette recorder is flown primarily for voice recording of
data but may also be used to play prerecorded tapes.  A microcassette
tape has a recording time of 30 minutes per side.  It is powered by
two 1.5-volt AAA alkaline batteries.


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WICKET TABS

Wicket tabs are devices that help the crew member activate controls
when his vision is degraded.  The tabs provide the crew member with
tactile cues to the location of controls to be activated as well as a
memory aid to their function, sequence of activation and other
pertinent information.  Wicket tabs are found on controls that are
difficult to see during the ascent and entry flight phases on panels
O8, C3 and R2.


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PHOTOGRAPHIC EQUIPMENT

Three camera systems-16mm, 35mm and 70mm-are used by the flight crew
to document activities inside and outside the orbiter.  All three
camera systems are used to document on-orbit operations.  The 16mm
camera is also used during the launch and landing phases of the
flight.

The 16mm camera is like a motion picture camera with independent
shutter speeds and frame rates.  The camera can be operated in one of
three modes: pulse, cine, or time exposure.  In the pulse mode, the
camera operates at a continuous frame rate of two, six or 12 frames
per second.  In the cine mode, the camera operates at 24 frames per
second.  In the time exposure mode, the first switch actuation opens
the shutter and the second actuation closes it.  The camera uses
140-foot film magazines and has 5mm, 10mm and 18mm lenses.

The 35mm camera is a motorized, battery-operated Nikon camera with
reflex viewing, through-the-lens coupled light metering and automatic
film advancement.  The camera has the standard manual operation and
three automatic (electrically controlled) modes-single exposure,
continuous and time.  It uses an f/1.4 lens.

The 70mm camera system is a modified battery-powered, motor-driven,
single-reflex Hasselblad camera that has 80mm and 250mm lenses and
film magazines.  Each magazine contains approximately 80 exposures.
This camera has only one mode of operation, automatic; however, there
are five automatic-type camera functions from which to select.  The
camera has a fixed viewfinder for through-the-lens viewing.

Interdeck light shades are provided to minimize light leakage between
the flight deck and middeck during in-cabin photography.  The light
shade is attached with Velcro to the middeck ceiling around the
interdeck access.  Adjustable louvers are provided to regulate the
amount of light between the flight deck and middeck.


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REACH AID

The reach aid, sometimes known as the ''swizzle stick,'' is a short
adjustable bar with a multipurpose end effector that is used to
actuate controls that are out of the reach of seated crew members.
The reach aid is used to push in and pull out circuit breakers and
move toggle switches.  It may be used during any phase of flight, but
is not recommended for use during ascent because of the attenuation
and switch-cuing difficulties resulting from acceleration forces.

Operation of the reach aid consists of extending it and actuating
controls with the end effector.  To extend the reach aid, one
depresses the spring-loaded extension tab and pulls the end effector
out to the desired length.


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RESTRAINTS AND MOBILITY AIDS

Restraints and mobility aids are provided in the orbiter to enable the
flight crew to perform all tasks safely and efficiently during ingress
(1-g, orbiter vertical), egress (1-g, orbiter horizontal) and orbital
flight (orbiter orientation arbitrary).  Restraints and mobility aids
consist of foot loop restraints, the airlock foot restraint platform
and the work/dining table.  In-flight restraints consist of temporary
stowage bags, Velcro, tape, snaps, cable restraints, clips, bungees
and tethers.

Mobility aids and devices consist of handholds, footholds, handrails,
ladders and the ingress-egress platform.

Foot loop restraints are cloth loops attached to the crew compartment
decks by adhesive to secure crew members to the deck.  Before launch,
the foot loop restraints are installed on the floor areas of the aft
flight deck work stations, middeck lockers, waste collection system
and galley (if installed).  Spares will be stowed in the modular
lockers.  To install a foot restraint, the protective backing on the
underside of the restraint is removed and the restraint is placed in
its desired location.  The foot loop restraints are easily used by
placing one or both feet in the loop.

The temporary stowage bag is used to restrain, stow or transport loose
equipment temporarily.  It is snapped or attached with Velcro to the
crew station standard Velcro and snap patterns.

Mobility aids and devices are located in the crew compartment for
movement of the flight crew members during ingress, egress and orbital
flight.  These devices consist of handholds for ingress and egress to
and from crew seats in the launch and landing configuration, handholds
in the primary interdeck access opening for ingress and egress in the
launch and landing configuration, a platform in the middeck for
ingress and egress to and from the middeck when the orbiter is in the
launch configuration, and an interdeck access ladder to enter the
flight deck from the middeck in the launch configuration and go from
the flight deck to the middeck in the launch and landing
configuration.

The flight data file is a flight reference data file that is readily
available to crew members aboard the orbiter.  It consists of the
onboard complement of documentation and related crew aids and includes
documentation, such as procedural checklists (normal, backup and
emergency procedures), malfunction procedures, crew activity plans,
schematics, photographs, cue cards, star charts, Earth maps and crew
notebooks; FDF stowage containers; and FDF ancillary equipment, such
as tethers, clips, tape and erasers.

Four permanently mounted containers are located to the left and right
side of the commander's and pilot's seats for stowing FDFs on the
flight deck.  The remaining FDF items are stowed in a middeck modular
stowage locker.

The flight data file quantity and stowage locations are similar for
all flights.  The baseline stowage volume is sufficient to contain all
FDF items for all orbiter configurations except the pallet-mounted
payload.  In this case, a larger flight data file and, consequently,
additional locker space are required because all payload operations
are performed in the orbiter.

FDF items are used throughout the flight-from prelaunch use of the
ascent checklist through crew use of the entry checklist.

Flight data files are packaged and stowed on an individual flight
basis.  FDF items will be stowed in five types of stowage containers:
lockers, the flight deck module, the commander's and pilot's seat-back
FDF assemblies, the middeck FDF assembly and the map bag.  The
portable containers are stowed in a middeck modular locker for launch
and entry.

If the flight carries a Spacelab module, all Spacelab books are stowed
for launch in a portable container on the middeck and transferred in
flight to the Spacelab.  The FDF stowage is flexible and easily
accessible.


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CREW EQUIPMENT STOWAGE

Crew equipment on board the orbiter is stowed in lockers with
insertable trays.  The trays can be adapted to accommodate a wide
variety of soft goods, loose equipment and food.  The lockers are
interchangeable and attach to the orbiter with crew fittings.  The
lockers can be removed or installed in flight by the crew members.
There are two sizes of trays: a half-size tray (two of which fit
inside a locker) and a full-size tray.  Approximately 150 cubic feet
of stowage space is available, almost 95 percent of it on the middeck.

The lockers are made of either epoxy- or polyimide-coated Kevlar
honeycomb material joined at the corners with aluminum channels.
Inside dimensions are approximately 10 by 17 by 20 inches.  The
honeycomb material is approximately 0.25 of an inch thick and was
chosen for its strength and light weight.  The lockers contain about 2
cubic feet of space and can hold up to 60 pounds.

Dividers are used in the trays to provide a friction fit for zero-g
retention.  This will reduce the necessity for the straps, bags,
Velcro snaps and other cumbersome attach devices previously used.
Soft containers will be used in orbiter spaces too small for the fixed
lockers.

The trays are packed with gear so that no item covers another type of
gear.  This method of packing will reduce the confusion usually
associated with finding loose equipment and maintaining a record of
the equipment.

Stowage areas in the orbiter crew compartment are located in the
forward flight deck, the aft flight deck, the middeck, the equipment
bay and the airlock module.

In the aft flight deck, stowage lockers are located below the rear
payload control panels in the center of the deck.  Container modules
can be mounted to the right and left of the payload control station.
Since these side containers are interchangeable, they may not be
carried on every mission, depending on any payload-unique installed
electronic gear.

In the middeck, container modules can be inserted in the forward
avionics bay.  Provisions for 42 containers are available in this
area.  In addition, there is an area to the right side of the airlock
module where nine containers can be attached.

Harness stowage bags stowed in a middeck stowage locker or airlock are
used on orbit to stow flight crew members' launch equipment, such as
helmets, harnesses, boots and waste/trash materials.


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EXERCISE EQUIPMENT

The only exercise equipment presently being flown is a treadmill.  The
exact stowage location in the crew compartment middeck for launch,
orbit and entry depends on the mission.

The treadmill is used with a restraint system to allow a crew member
to run or jog in orbit.  The treadmill kit is stowed on top of the
treadmill and contains the waist belt, two shoulder straps, four
extender hooks and a physiological monitor.  The treadmill kit is
restrained by four force cords that are used to restrain the body
during exercise.  The treadmill attaches to four middeck quick
disconnects.  The quick disconnects contain several metal hooks that
are hinged within the quick disconnect and actuated by the knurled
lock ring.  To release the quick disconnects, the lock push button is
depressed and the knurled lock ring is pushed up, releasing the metal
hooks.  When the lock ring is pushed down, the metal hooks converge
and capture the top of the middeck stud.

The treadmill has a speed control knob, which controls a rapid onset
braking system.  When the preset speed is reached, the brake engages
and produces increased drag on the running track.

The physiological monitor provides heart rate, the time run and the
distance run.  The heart rate is determined by an ear clip, which has
an infrared sensor that detects increased blood flow (pulses) in the
ear lobe.  Distance run is determined by connecting a mechanical
sensor wire on the side of the treadmill to the physiological monitor.
The mechanical sensor detects the number of revolutions of the track
and sends an electrical signal to the physiological monitor, where the
distance is computed and shown on the display along with the heart
rate.  The monitor is stowed on the treadmill handle while the crew
member runs.


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SOUND LEVEL METER

The sound level meter is provided to determine on-orbit acoustical
noise levels in the cabin.  Depending on the requirements for each
flight, the flight crew is required to take meter readings at
specified crew compartment and equipment locations.  The data obtained
by the flight crew is logged and/or voice recorded.  The meter is
operated by four 1.5-volt batteries.


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AIR SAMPLING SYSTEM

The air sampling system consists of air bottles that are stowed in a
modular locker.  They are removed for sampling and restowed for entry.