<table style="width:100%;">
<colgroup>
<col style="width: 9%" />
<col style="width: 8%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 29%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 4%" />
<col style="width: 0%" />
<col style="width: 0%" />
<col style="width: 13%" />
<col style="width: 6%" />
<col style="width: 9%" />
<col style="width: 16%" />
</colgroup>
<thead>
<tr class="header">
<th colspan="7"></th>
<th colspan="4"><strong>A. NUMBER</strong></th>
<th colspan="2"><strong>B. PHASE</strong></th>
<th><strong>C. DATE</strong></th>
</tr>
<tr class="odd">
<th colspan="7"><strong>F</strong><strong>LIGHT PAYLOAD STANDARDIZED
HAZARD CONTROL REPORT</strong></th>
<th colspan="3">STD-</th>
<th>AMS-02-F02</th>
<th colspan="2"><strong>Phase II</strong></th>
<th>May 25, 2007</th>
</tr>
<tr class="header">
<th colspan="7"><strong>D. PAYLOAD, DTO, DSO or RME</strong>
<em>(Include Part Number(s), if applicable)</em></th>
<th colspan="5"><strong>HAZARD TITLE</strong></th>
<th colspan="2"><strong>E. VEHICLE</strong></th>
</tr>
<tr class="odd">
<th colspan="7">Alpha Magnetic Spectrometer (AMS-02) Orbiter Interior
Elements–See Attached List</th>
<th colspan="5">STANDARD HAZARDS</th>
<th colspan="2"></th>
</tr>
<tr class="header">
<th colspan="4"><strong>F. DESCRIPTION OF HAZARD:</strong></th>
<th colspan="3"><strong>G. HAZARD CONTROLS:</strong> <em>(complies
with)</em></th>
<th colspan="3"><p><strong>H.</strong></p>
<p><strong>APP.</strong></p></th>
<th colspan="4"><strong>I. VERIFICATION METHOD, REFERENCE, AND
STATUS:</strong></th>
</tr>
</thead>
<tbody>
<tr class="odd">
<td colspan="4"><ol type="1">
<li><p>Structural Failure <em>(payloads</em></p></li>
</ol>
<p><em>must comply with the listed</em></p>
<p><em>requirements for all phases of</em></p>
<p><em>flight)</em></p>
<p><em>Note: Locker and Soft Stowage items only.</em></p></td>
<td colspan="3"><blockquote>
<p>Designed to meet the standard modular locker stowage requirements of
NSTS 21000-IDD-MDK or equivalent IDD <u>     </u> .</p>
</blockquote></td>
<td colspan="3"></td>
<td colspan="4"><p>1.1.1. SVM: Review of Installation drawings for
Middeck Stowage.</p>
<p>1.1.2. SVM: Weight/CG Analysis for Stowage for Middeck Stowage</p>
<p>1.1.1 STATUS: Open</p>
<p>1.1.2 STATUS: Open</p></td>
</tr>
<tr class="even">
<td colspan="4"><ol start="2" type="1">
<li><p>Structural Failure of Sealed Containers</p></li>
</ol>
<p><strong>Note 1: Only sealed containers made of conventional metal
(metal alloy) can use the 1230 form. Sealed containers made of
unconventional metals or non-metallic materials shall be documented on
Unique Hazard Reports.</strong></p>
<p><strong>Note 2: The 1230 form is not applicable for “sealed
container”(s) employed in levels of containment control of hazardous
fluid.</strong></p></td>
<td colspan="3"><blockquote>
<p>Sealed containers must meet the criteria of NASA-STD-5003, Para.
4.2.2.4.2.3a, contain a substance which is not a hazard if released, be
made of conventional metals (e.g. Al, inconel, monel, steel or
titanium), contain less than 14,240 foot-pounds (19,130 Joules) of
stored energy due to pressure, and have a maximum delta pressure of 1.5
atm.</p>
</blockquote></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. – No Sealed Containers used as
structure (No Sealed Containers for any purpose)</td>
</tr>
<tr class="odd">
<td><strong>APPROVAL</strong></td>
<td colspan="8"><strong>PAYLOAD ORGANIZATION</strong></td>
<td colspan="5"><strong>SSP/ISS</strong></td>
</tr>
<tr class="even">
<td><strong>PHASE I</strong></td>
<td colspan="8"><strong>     </strong></td>
<td colspan="5"><strong>     </strong></td>
</tr>
<tr class="odd">
<td><strong>PHASE II</strong></td>
<td colspan="8"><strong>     </strong></td>
<td colspan="5"><strong>     </strong></td>
</tr>
<tr class="even">
<td><strong>PHASE III</strong></td>
<td colspan="8"><strong>     </strong></td>
<td colspan="5"><strong>     </strong></td>
</tr>
<tr class="odd">
<td colspan="4"><ol start="3" type="1">
<li><p>Structural Failure of Vented Containers</p></li>
</ol></td>
<td colspan="3"><blockquote>
<p>For intentionally vented containers, vents are sized to maintain a
1.4 factor of safety for Shuttle or a 1.5 factor of safety for Station
with respect to pressure loads. Meets all of the applicable pressure
rates defined for one or more of the following.</p>
</blockquote>
<ol type="a">
<li><p>Shuttle payload bay – ICD 2-19001, Para. 10.6.1</p></li>
</ol>
<p>b) Station environment – SSP 52005, paragraph</p>
<blockquote>
<p>4.3 or equivalent payload specific ICD <u>     </u>.</p>
</blockquote>
<p>c) Station PFE discharge – SSP 57000, Para.</p>
<blockquote>
<p>3.1.1.4K, or equivalent payload specific ICD <u>     </u>.</p>
</blockquote>
<p>d) Shuttle Middeck – NSTS 21000-IDD-MDK, Section 6.1.</p></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. – No confined volumes in hardware
design.</td>
</tr>
<tr class="even">
<td colspan="4"><ol start="4" type="1">
<li><p>Sharp Edges, Corners,</p></li>
</ol>
<p>and/or Protrusions.</p></td>
<td colspan="3"><p>Meets the <strong><u>intent</u></strong> of one or
more of the following:</p>
<ol type="a">
<li><p>NASA-STD-3000 / SSP 50005</p></li>
<li><p>SLP 2104</p></li>
<li><p>NSTS 07700 Vol. XIV App. 7 (EVA hardware)</p></li>
<li><p>NSTS 07700 Vol. XIV App. 9 (IVA hardware) / SSP 57000</p></li>
</ol>
<p>e) SSP 41163, Para. 3.3.6.12.3 (EVA), Para. 3.3.6.12.4
(IVA).</p></td>
<td colspan="3"></td>
<td colspan="4"><p>4.a.1 SVM: Inspection of flight hardware for sharp
edges, corners and protrusions.</p>
<p>4.a.1 STATUS: Open</p></td>
</tr>
<tr class="odd">
<td colspan="4">5. Shatterable Material Release</td>
<td colspan="3"><ol type="a">
<li><p>All materials are contained.</p></li>
<li><p>Optical glass (i.e. lenses, filters, etc.) components of crew
cabin experiment hardware that are non-stressed (no delta pressure) and
have passed both a vibration test at flight levels and a post-test
visual inspection.</p></li>
<li><p>Payload bay hardware shatterable material components that weigh
less than 0.25 lb and are non-stressed (no delta pressure) or
non-structural.</p></li>
</ol></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. No Identified Shatterable
Materials</td>
</tr>
<tr class="even">
<td colspan="4">6. Flammable Materials</td>
<td colspan="3"><ol type="a">
<li><p>A-rated materials selected from MAPTIS, or</p></li>
<li><p>Flammability assessment per NSTS 22648</p></li>
</ol></td>
<td colspan="3"></td>
<td colspan="4"><p>6.b.1 SVM: Review of design for appropriate use of
non-flammable materials.</p>
<p>6.b.2 SVM: Review and approval of flammability assessment by
JSC/ES4.</p>
<p>6.b.1 STATUS: Open</p>
<p>6.b.2 STATUS: Open</p></td>
</tr>
<tr class="odd">
<td colspan="4">7. Materials Offgassing</td>
<td colspan="3"><blockquote>
<p>Offgassing tests of assembled article per NASA-STD-6001 (previously
published as NHB 8060.1C).</p>
</blockquote></td>
<td colspan="3"></td>
<td colspan="4">Reference Hazard Report AMS-02-F02</td>
</tr>
<tr class="even">
<td colspan="4"><p>8. Nonionizing Radiation</p>
<p>8.1 Non-transmitters</p></td>
<td colspan="3"><p>Meets all that apply:</p>
<ol type="a">
<li><p>Pass ICD-2-19001, 10.7.3.2.2 / SSP 30238 EMI compatibility
testing, or</p></li>
<li><p>NSTS/USA approved analysis ICD Section 20, or</p></li>
<li><p>ISS/EMEP approved TIA</p></li>
<li><p>Meets SSP 41163, Para. 3.3.6.6 <strong>and</strong> SSP 50094,
Para. 3.4.</p></li>
</ol></td>
<td colspan="3"></td>
<td colspan="4"><p>8.1.a.1 SVM: EMI testing results reviewed and
approved by JSC/EV4</p>
<p>8.1.a.1 STATUS: Open</p></td>
</tr>
<tr class="odd">
<td colspan="4"><ol start="2" type="1">
<li><p>Lasers</p></li>
</ol>
<p><strong>NOTE: Lasers operating at class levels 3b and 4, meeting ANSI
Z136.1, shall be documented on Unique Hazard Reports.</strong></p></td>
<td colspan="3"><p>Meet ANSI Z136.1-2000 for class 1, 2, or 3a
Lasers</p>
<p>(as measured at the source).</p></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. Internal elements of AMS-02 do not
generate coherent light.</td>
</tr>
<tr class="even">
<td colspan="4">9.1 Alkaline cells and batteries made of alkaline cells,
connected in series or in parallel, up to 12 V and with up to 60
Watt-hours capacity, no potential charging source and cells are not in a
gas-tight compartment.</td>
<td colspan="3">Cells and batteries pass acceptance tests that include
loaded and open circuit voltage measurements, visual examination, and
leakage check under vacuum (e.g. 6 hours at 0.1 psia).</td>
<td colspan="3"></td>
<td colspan="4"><p><strong>N/A</strong>. AMS-02 Interior elements
utilize no batteries.</p>
<p>Submission of EP-Form-03(including the form’s approved reference
number) for EP5 approval</p>
<p>Information to be included on the EP5 reviewed/approved Form-03:
application and protective circuit schematics</p></td>
</tr>
<tr class="odd">
<td colspan="4">9.2 Primary button cells such as Li-(CF)x, Li-iodine,
LiV<sub>2</sub>O<sub>5</sub>, LiMnO<sub>2</sub>, Ag-Zn and rechargeable
button cells such as LiV<sub>2</sub>O<sub>5</sub>, Li-ion, Ni-Cd, Ni-MH,
Ag-Zn cells or batteries, which have a capacity of 300 mAh or less and
no more than 3 cells per common circuit, and cells are not in a
gas-tight compartment.</td>
<td colspan="3"><p>Cells and batteries pass acceptance tests that
include loaded and open circuit voltage measurements, visual
examination, and leakage check under vacuum (e.g. 6 hours at 0.1
psia).</p>
<p>Note: Above acceptance testing for button cells in Section 9.2 which
are soldered to a circuit board in commercial equipment (not applicable
to those button cells in a spring-loaded clip) is limited to a
functional check of the equipment utilizing the subject
battery.</p></td>
<td colspan="3"></td>
<td colspan="4"><p><strong>N/A</strong>. AMS-02 Interior elements
utilize no batteries.</p>
<p>Submission of EP-Form-03(including the form’s approved reference
number) for EP5 approval</p>
<p>Information to be included on the EP5 reviewed/approved Form-03::
application and protective circuitry.</p></td>
</tr>
<tr class="even">
<td colspan="4">9.3 COTS NiMH, NiCd and Ag/Zn cells and batteries for
IVA use up to 20 V and 60 Wh</td>
<td colspan="3">Cells and batteries purchased in one lot; pass
acceptance tests that include loaded and open circuit voltage
measurements, visual examination, leakage check under vacuum (e.g 6
hours at 0.1psia) and vibration to workmanship levels with functional
checks which include charge/discharge cycles for rechargeable
batteries.</td>
<td colspan="3"></td>
<td colspan="4"><p><strong>N/A</strong>. AMS-02 Interior elements
utilize no batteries.</p>
<p>Submission of EP5 Form-03(including the form’s approved reference
number) for approval</p>
<p>Information to be included on the EP5 reviewed/approved Form-03:
manufacturer’s specification, battery protective features and charger
schematics</p></td>
</tr>
<tr class="odd">
<td colspan="4">9.4 COTS Li-ion batteries up to 10 V and 60 Wh for IVA
use</td>
<td colspan="3">Batteries and charger shall be from a single lot; shall
show one-fault tolerance at battery level and shall pass acceptance
tests that include loaded and open circuit voltage measurements, visual
examination, leakage check under vacuum (e.g 6 hours at 0.1psia) and
vibration to environment or double the workmanship level, whichever is
higher; and functional checks which include charge/discharge
cycles.</td>
<td colspan="3"></td>
<td colspan="4"><p><strong>N/A</strong>. AMS-02 Interior elements
utilize no batteries.</p>
<p>Submission of EP-Form-03(including the form’s approved reference
number) for EP5 approval.</p>
<p>Information to be included on the EP5 reviewed/approved Form-03:
battery protective features and charger features</p>
<p>Note: For hardware using batteries, and/or chargers additional levels
of control shall be provided by the hardware</p>
<p>.</p></td>
</tr>
<tr class="even">
<td colspan="4">10. Touch Temperature</td>
<td colspan="3"><ol type="a">
<li><p>Within IVA touch temperature range of –18 Degrees C. (0 Degrees
F.) and 49 Degrees C. (120 Degrees F.) and satisfies the intentional
contact constraints of letter MA2-95-048 (if applicable).</p></li>
<li><p>Meets EVA touch temperature criteria of NSTS 07700 Vol. XIV App.
7.</p></li>
</ol></td>
<td colspan="3"></td>
<td colspan="4"><p>10.a.1 SVM: Review of design to confirm power
consuming elements inaccessible to the crew.</p>
<p>10.a.2 SVM: Analysis to confirm that interface card will not induce
excessive thermal load on PGSC/NGLS.</p>
<p>10.a.1 STATUS: Open</p>
<p>10.a.2 STATUS: Open</p></td>
</tr>
<tr class="odd">
<td colspan="4">11. Electrical Power Distribution</td>
<td colspan="3"><ol type="a">
<li><p>Shuttle-powered payloads – Meets all circuit protection
requirements of Letter TA-92-038.</p></li>
<li><p>Station-powered payloads – Meets station interface circuit
protection requirements of SSP 57000 and payload circuit protection
requirements of Letter TA-92-038.</p></li>
</ol></td>
<td colspan="3"></td>
<td colspan="4"><p>11.a.1 SVM: Review of Design</p>
<p>11.a.1 STATUS: Open</p>
<p>Note: The USB422 makes its interface is with the PGSC/NGLS and is not
directly interfaced with the Shuttle power systems.</p></td>
</tr>
<tr class="even">
<td colspan="4"><p>12. Ignition of Flammable</p>
<p>Atmospheres in Payload Bay</p></td>
<td colspan="3"><blockquote>
<p>All ignition sources in the Payload bay, for launch and landing, are
controlled as required in Letter NS2/81-MO82, and MLI grounded per ICD
2-19001.</p>
</blockquote></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. Hardware addressed in this hazard
report is within the crew habitable environment and not exposed to a
flammable atmosphere in the Shuttle Payload Bay</td>
</tr>
<tr class="odd">
<td colspan="4">13. Rotating Equipment</td>
<td colspan="3"><blockquote>
<p>Rotating equipment meets criteria of NASA-STD-5003 for obvious
containment.</p>
</blockquote></td>
<td colspan="3"></td>
<td colspan="4"><strong>N/A</strong>. AMS-02 Internal hardware does not
utilize any rotating equipment.</td>
</tr>
<tr class="even">
<td colspan="2"><p>14. Mating/demating powered</p>
<p>connectors</p></td>
<td colspan="3"><ol type="a">
<li><p>Meets the low power criteria of letter MA2-99-170 or,</p></li>
</ol>
<p>b) Meets the paragraph 1 criteria of letter MA2-99-170</p>
<p>(e.g., IVA and open circuit voltage no greater than</p>
<p>32 volts).</p></td>
<td colspan="3"></td>
<td colspan="6"><p>14.a.1 SVM: Review of Design. T</p>
<p>14.a.1 STATUS: Open</p></td>
</tr>
<tr class="odd">
<td colspan="3">15. Contingency Return and Rapid Safing</td>
<td colspan="3"><blockquote>
<p>Shuttle Environment:</p>
</blockquote>
<ol type="a">
<li><p>If middeck payload – can be stowed within 50 min.</p></li>
</ol>
<p>(see paragraph 3 of letter MA2-96-190).</p>
<p>b) If SPACEHAB transfer item – can establish a safe for return
configuration within 3 min. (see paragraph 5 of letter MA2-96-190).</p>
<blockquote>
<p>Station Environment:</p>
</blockquote>
<p>c) Payload design does not impede emergency IVA egress to the
remaining adjacent pressurized volumes.</p></td>
<td colspan="3"></td>
<td colspan="5"><p>15a.1 SVM: Rapid Safing Assessment to establish that
the PGSC/NGLS and data cables can be stowed within 50 minutes.</p>
<p>15.a.1 STATUS: Open</p></td>
</tr>
<tr class="even">
<td colspan="3">16. Release of Mercury from bulbs into crew habitable
environment.</td>
<td colspan="3"><p>a) Mercury vapor bulbs contain less than 30 mg of</p>
<blockquote>
<p>Mercury per bulb, and</p>
</blockquote>
<ol start="2" type="a">
<li><p>No more than one bulb could break due to a single</p></li>
</ol>
<p>failure.</p></td>
<td colspan="3"></td>
<td colspan="5"><strong>N/A</strong>. AMS-02 internal hardware elements
do not utilize mercury containing bulbs.</td>
</tr>
</tbody>
</table>

**Alpha Magnetic Spectrometer --02 (AMS-02) Orbiter Interior Hardware
Elements:**

-   DDRS-02 Elements

    -   Digi USB422 Interface (interface for PGSC/NGLS USB connectivity)

    -   USB422 to PDIP Cables P/N SED 3939136111

    -   COTS USB A-B cable, wrapped in Teflon tape (connects USB422 to
        PGSC/NGLS)

> NOTE:

-   *Payload General Support Equipment (PGSC)/ Next Generation Laptop
    System (NGLS)***, not considered in STD-AMS-02-02, GFE is being used
    in accordance with its GFE certification.**

-   *Spare Hard Disk (GFE) for PGSC/NGLS***, not considered in
    STD-AMS-02-02, GFE is being used in accordance with its GFE
    certification.**

-   Other Hardware

    -   Cable SED 39136112-301 -- PDIP J103 to J105 Patch Cable --
        Patches RS422 to T0 umbilical for GSE monitoring and control of
        the AMS-02 prior to launch.

### 

+-----------------------+----------------------------------------------+
| ### About USB422      | ### ![](media/image1.jpeg){width="6.18194    |
|                       | 44444444445in" height="4.620138888888889in"} |
| The USB422 interface  |                                              |
| provides inline       | ### Picture is re                            |
| conversion of RS422   | presentation of USB422 and Non-Flight cables |
| synchronous serial    |                                              |
| signals to a USB 2.0  |                                              |
| interface. The unit   |                                              |
| is powered by the USB |                                              |
| 5.0 volt bus provided |                                              |
| power and draws less  |                                              |
| the 0.5 amp. USB422   |                                              |
| is a single PCB based |                                              |
| on a Cypress FX2 chip |                                              |
| and a gate array.     |                                              |
| This card will be     |                                              |
| hand conformal coated |                                              |
| with Dow Corning 3140 |                                              |
| or equivalent.        |                                              |
|                       |                                              |
| USB422 is housed in a |                                              |
| rugged aluminum       |                                              |
| enclosure with Twinax |                                              |
| style connections on  |                                              |
| one end and a         |                                              |
| commercial USB cable  |                                              |
| Teflon wrapped on the |                                              |
| other. The USB cable  |                                              |
| plugs into the NGLS   |                                              |
| USB connection and is |                                              |
| strain relieved by a  |                                              |
| Velcro strap to the   |                                              |
| power connection      |                                              |
| cable (TBC).          |                                              |
+-----------------------+----------------------------------------------+

+-----------------------------------------------------------------------+
| ![](media/image2.wmf){width="9.446527777777778in"                     |
| height="3.0388888888888888in"}                                        |
+-----------------------------------------------------------------------+
| **DDRS-02 -- Cable RS422 to PDIP (P/N SED 3939136111)**               |
+-----------------------------------------------------------------------+
| ![](media/image3.wmf){width="9.455555555555556in"                     |
| height="2.7423611111111112in"}                                        |
+-----------------------------------------------------------------------+
| **DDRS-02 Cable -- RS422 to PDIP Schematic**                          |
+-----------------------------------------------------------------------+
| ![](media/image4.wmf){width="9.534027777777778in"                     |
| height="2.7715277777777776in"}                                        |
+-----------------------------------------------------------------------+
| PDIP J103 to J105 Patch Cable (SED 39136112-301)                      |
|                                                                       |
| NOTE: Dimensions are not accurately reported in this preliminary      |
| drawing, final length should be approximately 12 inches.              |
+-----------------------------------------------------------------------+
| ![](media/image5.wmf){width="9.54513888888889in"                      |
| height="2.9472222222222224in"}                                        |
+-----------------------------------------------------------------------+
| PDIP J103 to J105 Patch Cable Schematic                               |
+-----------------------------------------------------------------------+