![](media/image1.wmf){width="0.9375in" height="0.8041666666666667in"}

Multi-Layer Insulation for the Alpha Magnetic Spectrometer

*Guidelines*

CTSD-SH-1782

Revision A

Crew and Thermal Systems Division

June 19, 2007

![](media/image3.wmf)

# Table of Contents {#table-of-contents .unnumbered}

[Table of Contents ii](#table-of-contents)

[list of tables iv](#list-of-tables)

[list of Figures v](#list-of-figures)

[acronyms AND ABBREVIATIONS vi](#acronyms-and-abbreviations)

[1 Introduction 1](#introduction)

[1.1 PURPOSE 1](#purpose)

[1.2 SCOPE 1](#scope)

[1.3 Multi-layer insulation for the Ams Project description
1](#multi-layer-insulation-for-the-ams-project-description)

[1.4 APPLICABILITY 2](#applicability)

[2 REFERENCE documents 3](#reference-documents)

[3 requirements 4](#requirements)

[3.1 operational requirements 4](#operational-requirements)

[3.1.1 Thermal Environment 4](#thermal-environment)

[3.1.2 Depressurization and Repressurization Rates
4](#depressurization-and-repressurization-rates)

[3.1.3 Radiation 6](#radiation)

[3.1.4 Solar Electromagnetic Radiation
6](#solar-electromagnetic-radiation)

[3.2 QUALITY ASSURANCE PROVISIONS 6](#quality-assurance-provisions)

[3.3 non-operational requirements 7](#non-operational-requirements)

[3.3.1 In Fabrication Handling 7](#in-fabrication-handling)

[3.3.2 Storage 7](#storage)

[3.3.3 Handling during Installation 8](#handling-during-installation)

[3.3.4 Repair 8](#repair)

[3.4 MAINTAINABILITY and RELIABILITY
8](#maintainability-and-reliability)

[3.4.1 Useful Life 9](#useful-life)

[3.4.2 Shelf Life 9](#shelf-life)

[3.4.3 Acceptance 9](#acceptance)

[3.4.4 Documentation 9](#documentation)

[4 Materials Specifications 10](#materials-specifications)

[4.1 MLI Structure 10](#mli-structure)

[4.2 Electrical Bonding and Grounding
11](#electrical-bonding-and-grounding)

[4.3 Venting 12](#venting)

[4.4 Standard MLI 12](#standard-mli)

[4.5 MLI BLANKETS FABRICATION 13](#mli-blankets-fabrication)

[5 CLEAN ROOM 14](#clean-room)

[6 ATTACHMENT 15](#attachment)

[7 DELIVERABLES 16](#deliverables)

# list of tables {#list-of-tables .unnumbered}

Table 1: Typical MLI Lay-up Materials. 12

Table 2: Typical MLI Joining Materials 13

Table 3: ISO Class 8 Clean Room 14

# list of Figures {#list-of-figures .unnumbered}

Figure 1: Orbiter Cargo Bay Internal Pressure History during Ascent 5

Figure 2: Entry Phase Cargo Bay Internal Pressure Profile 6

# acronyms AND ABBREVIATIONS {#acronyms-and-abbreviations .unnumbered}

AMS Alpha Magnetic Spectrometer

CCB Configuration Control Board

CO~2~ Carbon Dioxide

CTSD Crew and Thermal Systems Division

EA Engineering Directorate

ESA European Space Agency

ISS International Space Station

JSC Johnson Space Center

MLI Multi-layer Insulation

NASA National Aeronautics and Space Administration

PET Polyethylene Terephthalate (Mylar)

PIH Payload Integration Hardware

PSA Pressure Sensitive Adhesive

PTFE Polytetrafluoroethylene (Teflon)

PVU Prototype Verification Unit

RH Relative Humidity

SPI Stitches per Inch

T Temperature

TCS Thermal Control System

VCM Volatile Condensable Material

Xe Xenon

# Introduction 

## PURPOSE {#purpose .Style-Heading-2-+-Arial-12-pt}

This document provides the guidelines for the fabrication, handling,
storage, and repair of multi-layer insulation (MLI) for the Alpha
Magnetic Spectrometer Project. The contents of this document should be
used as the basis for the manufacturing and integration of all MLI on
the Alpha Magnetic Spectrometer -- 02 (AMS-02).

## SCOPE {#scope .Style-Heading-2-+-Arial-12-pt}

This document delineates the requirements for the fabrication,
containment, storage, installation, repair and inspection of MLI
blankets used on the AMS-02 Payload. Guidelines for materials selection,
operational and non-operational environments and design and construction
standards are also included in this document.

## Multi-layer insulation for the Ams Project description {#multi-layer-insulation-for-the-ams-project-description .Style-Heading-2-+-Arial-12-pt}

In accordance with JSC 29789, Project Technical Requirements
Specification for the Alpha Magnetic Spectrometer -- 02 (AMS-02) Payload
Integration Hardware (PIH), thermal blankets will be used in conjunction
with the thermal control system (TCS) to protect AMS-02 components from
temperature extremes. Standard NASA MLI will be used for fabrication of
the thermal blankets. Standard MLI blankets are high-performance
insulators which are made of multiple layers of materials that retard
the flow of energy due to radiation heat transfer. They are usually made
of a plastic film (polyester or polyimide) with vapor deposited layers
of metal (most commonly aluminum) on one or both sides of the plastic
film to form reflector layers. These reflectors are separated by
materials with low thermal conductivity. Multi-layer insulation requires
an atmospheric pressure of less than 10^-5^ Torr to prevent convection
and gas conduction between the reflector layers. In general, the MLI is
externally protected from UV, atomic oxygen, and mechanical stresses by
a Teflon-coated fiberglass cloth. A single metallized polyimide (Kapton)
layer with the metal facing inward is placed just under the fiberglass
cloth to act as a light block.

## APPLICABILITY {#applicability .Style-Heading-2-+-Arial-12-pt}

The elements of these design guidelines must be observed by engineers
and technicians who design and manufacture MLI blankets for installation
on AMS-02.

If compliance to these guidelines is not possible, the AMS-02 waiver and
deviation process shall be used to document the non-conformance. Waivers
and deviations must be approved by the AMS Configuration Control Board
(CCB).

Revisions and changes to this document shall be made in accordance with
JSC 27542, Alpha Magnetic Spectrometer -- 02 (AMS-02) Configuration
Management Plan.

# REFERENCE documents

**Applicable Documents**

JSC 27296 Project Plan for the AMS-02

JSC 27542 Alpha Magnetic Spectrometer -- 02 (AMS-02) Configuration
Management Plan

JSC 63123 Alpha Magnetic Spectrometer -- 02 (AMS-02) Assembly and
Testing Integration Plan

JSC 63164 Quality Management Plan for the Alpha Magnetic Spectrometer
(AMS-02) Experiment

NSTS-21000- Space Shuttle Program-to-Space Station Program Interface

IDD-ISS Definition Document

**Reference Documents**

NASA/TP- Multilayer Insulation Material Guidelines

1999-209263

KSC KTI-5212 Material Selection List for Plastic Films, Foams, and
Adhesive Tapes

**Requirements Documents**

JSC 29789 Project Technical Requirements Specification for the Alpha
Magnetic Spectrometer -- 02 (AMS-02) Payload Integration Hardware (PIH)

JSC 28792 Alpha Magnetic Spectrometer -- 02 Structural Verification Plan
for the Space Transportation System and the International Space Station

SSP 30245 Space Station Electrical Bonding Requirements

# requirements

This section presents the requirements that are considered in
delineating the guidelines for the MLI blankets. Details about the MLI
blankets that meet the defined requirements are given in section 7,
Materials Specification.

## operational requirements {#operational-requirements .Style-Heading-2-+-Arial-12-pt}

The following paragraphs provide the operational requirements that are
applicable to all MLI blankets used on the AMS-02 Payload.

### Thermal Environment {#thermal-environment .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

The MLI blankets shall be designed to withstand the thermal extreme
conditions of -150º C to + 120º C. Verification shall be by test or
analysis.

Rationale 1: For unproven materials, tests shall be conducted to
demonstrate that the materials meet the above thermal range limits.

Rationale 2: For proven materials, analysis should be sufficient to
establish that this requirement is met.

### Depressurization and Repressurization Rates {#depressurization-and-repressurization-rates .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

The MLI shall withstand exposure to rapid depressurization or
repressurization rates of NSTS-21000-IDD-ISS, Sections 10.6.1.2
(Depressurization) and 10.6.1.3 (Repressurization). Verification shall
be by test or analysis.

Rationale 1: For unproven materials, the material composition must be
shown to meet this requirement.

Rationale 2: For proven materials, analysis should be sufficient to
establish that the requirement is met.

Depressurization rate charts are provided in Figures 1 and 2.

![](media/image4.wmf){width="4.489583333333333in" height="5.53125in"}

**Figure 1: Orbiter Cargo Bay Internal Pressure History during Ascent**

![](media/image5.wmf){width="3.53125in" height="4.322916666666667in"}

**Figure 2: Entry Phase Cargo Bay Internal Pressure Profile**

### Radiation {#radiation .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

MLI blankets that are directly exposed to UV radiation and atomic oxygen
shall have a UV radiation and atomic oxygen resistant outer cover.

### Solar Electromagnetic Radiation {#solar-electromagnetic-radiation .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

MLI exposed to the entire solar electromagnetic spectrum shall not
embrittle or show significant changes in physical properties during its
useful life as defined in paragraph 3.4.1.

## QUALITY ASSURANCE PROVISIONS {#quality-assurance-provisions .Style-Heading-2-+-Arial-12-pt}

The MLI shall be designed and fabricated in accordance with JSC 63164,
Quality Management Plan for the Alpha Magnetic Spectrometer (AMS-02)
Experiment.

## non-operational requirements {#non-operational-requirements .Style-Heading-2-+-Arial-12-pt}

### In Fabrication Handling {#in-fabrication-handling .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

Construction and assembly of the AMS MLI blanket panels will be done in
a conventional ISO Class 8 clean room. In addition to construction,
including joining panels together and assembly, disassembly or testing
of MLI blankets will be performed in a work area that has minimal dust,
particulate material, and condensate fumes. All tools, work tables,
equipment, templates, holding fixtures, sewing machines or other
structures that may contact the MLI must be cleaned before use with a
solvent having a nonvolatile residue not exceeding 0.02 g/L.
Compatibility of solvents with MLI materials and surfaces that may
contact MLI materials must be assessed before use. Work tables and
sewing machines should be protected with clean protective covers when
not in use.

Workers must wear clean laboratory smocks, powder-free latex gloves (or
clean white gloves) and footwear when handling and working with MLI.
Clean room clothing will be kept in the laboratory change/locker area
when not in use. Appropriate lint-free disposable protective clothing
and footwear may also be used. Large pieces of equipment being moved
into the clean room must be thoroughly vacuumed prior to entry.

### Storage {#storage .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

Raw materials are to remain in their protective packaging until ready
for use. Remove the materials from the protective packaging in the clean
room just prior to blanket fabrication. When not in use, cover or re-bag
these materials to maintain cleanliness. During nonworking hours, cover
blankets in fabrication with non-contaminating plastic sheets. Purge all
finished blankets with dry nitrogen and double bag the blankets in
protective packaging with heat-sealed edges for storage. Do not open
packaging that contains Class I (flight hardware) MLI blankets in an
area that is not environmentally controlled.

Raw materials and completed blankets should be stored at temperatures
between 10° C -- 35° C (50° F -- 95° F) to the maximum extent
practicable. Moisture absorbing desiccant packs and a humidity indicator
may be used between inner and outer storage bags to control and monitor
humidity levels during storage.

When blankets are removed for use, perform an inspection of the
protective packaging and the blanket for discoloration and damage that
may have occurred during transportation or storage.

### Handling during Installation {#handling-during-installation .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

The flight blankets must be removed from their protective packaging in a
clean area.

[Note]{.underline}: Use of a standard clean room or equivalent is only
requested for MLI blanket fabrication. Installation of the manufactured
blankets does not require standard clean room or equivalent conditions,
however blankets should be installed in a work area that is visibly
clean and free from particulate matter.

### Repair {#repair .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

Repairs to damaged blankets before final installation on the AMS-02
Payload should be done in controlled clean area. Repair to blankets
during and after assembly may be done on the assembled article if the
location and extent of damage permits such a repair. In all other cases,
the MLI should be removed for repair or replacement.

Small cuts or abraded areas on metallized surfaces may be repaired with
a contact-adhesive aluminized tape free of wrinkles. Verify that the
shelf life of the pressure sensitive adhesive (PSA) tape is within
limits before use. While making repairs, avoid entrapment of bubbles,
streaks, and foreign material under the tape.

The bagged MLI blankets must be transported in crates sized to hold the
blankets flat in the case of small panels or specifically designed to
hold more complex shapes.

## MAINTAINABILITY and RELIABILITY {#maintainability-and-reliability .Style-Heading-2-+-Arial-12-pt}

### Useful Life {#useful-life .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

The on-orbit life expectancy of the AMS-02 MLI blankets should be no
less than 5 years in operational condition, and no less than 15 years in
non-operational condition. In addition, the AMS-02 MLI blankets should
meet ISS contamination requirements as long as the payload is on-orbit.

### Shelf Life {#shelf-life .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

The shelf life of the AMS-02 non-reinforced (with no adhesive) MLI
blankets should be at least 15 years from the date of manufacture in
clean environment and while being stored in sealed protective packaging
under controlled storage conditions. Strong, durable protective film as
listed on NASA-KSC KTI-5212, Group 1 should be used for MLI packaging.
Shelf life should be guaranteed from date of manufacture when MLI is
stored in its original container between 50° F and 95° F (10° C and 35°
C) and at 50% relative humidity or less.

### Acceptance {#acceptance .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

Acceptance shall be by review of design and by inspection.

### Documentation {#documentation .Style-Heading-3-+-Arial-12-pt-Not-All-caps}

Documentation shall be provided in accordance with JSC 63164, Quality
Management Plan for the AMS-02 Experiment, Paragraph 5.11, Documented
History.

# Materials Specifications

The multi-layer reflective insulation blankets shall be made of
metallized plastics such as aluminized polyester film.

## MLI Structure {#mli-structure .Style-Heading-2-+-Arial-12-pt}

A typical MLI blanket should include:

• **Standard Blanket Layers^1^**

> -- Outer cover
>
> -- Light Blocker
>
> -- Reflector layers
>
> -- Separator layers
>
> -- Inner cover

• **Threads^2^**

> -- Non exposed seams
>
> -- Exposed Seams

• **Adhesives**

• **Adhesive Tapes**

• **Hook-and-Loop Fasteners**

• **Laces and Hand Ties**

• **Buttons**

• **Grommets**

^1^ Perforated or porolated reflector layers (15-20 for long term use).
Actual number of reflector layers shall be specified by the end user
(Detector or Subsystem Group).

^2^ The following guidelines should be observed for the joining of MLI
materials using sewn seams

-   Minimal number of seams to prevent heat shorts

-   Low stitch density for sewn seams: 4 to 8 stitches per inch (SPI)

-   Staggered seams

-   PTFE (Teflon) coated glass thread for seams exposed to the
    environment

## Electrical Bonding and Grounding {#electrical-bonding-and-grounding .Style-Heading-2-+-Arial-12-pt}

Electrical bonding and grounding will be provided by metallized tape
and/or grommets

A.  Resistance of grounding assemblies (per NASA/TP-1999-209263 and
    SSP-30245):

    a.  Resistance from ground to spacecraft structure shall be less
        than (\<) 1 Ohm

    b.  Resistance from aluminized surface to ground shall be less than
        (\<) 5,000 Ohms

    c.  An Ohmmeter shall be used to measure the above resistance.

```{=html}
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```
A.  Quantities of grounding assemblies per blanket is based on surface
    area (S.A.):

    a.  S.A. \<100 cm^2^: No grounding assemblies

    b.  100 cm^2^ \< S.A. \< 4 m^2^:  Two (2) grounding assemblies

    c.  4 m^2^ \< S.A.:  \> Two (2) grounding assemblies, as determined
        from the resistance measurement with the Ohmmeter, such that the
        minimum resistance requirement defined above is complied with.

B.  Aluminized Glass Cloth Outer Layer/Light Block:

    a.  The aluminized surface of the first reflective layer shall face
        the aluminized side of the glass cloth without any intervening
        material (scrim). This intermittent, uncontrolled contact is
        adequate for grounding the outer layer.

The number of grounding assemblies required must be determined from the
resistance measurement with the Ohm meter. Grounding assemblies shall
not keep blankets from meeting thermal requirements. Ground locations
shall be at least 2.54 cm (1 in.) away from other fasteners, and the
blanket assembly may not be welded together in the grounding area.

Grommets shall be made of corrosion resistant steel without coating as
specified in NASA/TP-1999-209263. The bolt must pass through a flat
washer, an eyelet terminal, the blanket, another flat washer, a lock
washer, and a lock nut. A single conductor wire of length determined by
the application must be crimped to the eyelet terminal and attached to
the ground. Use a 22 gauge grounding wire insulated by Teflon.

## Venting {#venting .Style-Heading-2-+-Arial-12-pt}

MLI blankets should be designed so that all trapped gases can be vented
to the atmosphere within 48 hours after launch. The vent paths should
not provide a return path for sunlight.

## Standard MLI  {#standard-mli .Style-Heading-2-+-Arial-12-pt}

Typically MLI blankets have a protective outer cover, a series of
reflector layers alternating with separator layers, and an inner layer.
A light block layer is usually added to blankets that are fully exposed
to the environment. The cover and light block layers may be combined
into one layer of aluminized glass fiber fabric if this material is
encapsulated with additional layers of other material on the aluminum
side.

The materials listed in tables 1 and 2 are acceptable for use in AMS-02
blankets. Other acceptable materials are listed in ESA PSS-01-701.

Table 1: Typical MLI Lay-up Materials

+--------------+-------------+-------------+-------------+------------+
| **Layer**    | *           | *           | **Suggested | **Product  |
|              | *Material** | *Applicable | Vendors**   | Name**     |
|              |             | Specs**     |             |            |
+--------------+-------------+-------------+-------------+------------+
| Cover        | Glass fiber | MBO135-027  | Bron Tapes  | Beta       |
|              | fabric      |             |             | fabric     |
|              |             |             |             | 500F       |
+--------------+-------------+-------------+-------------+------------+
| Light Block  | Aluminized  |             | Dunmore     |            |
|              | polyimide   |             |             |            |
|              |             |             | Sheldahl    |            |
|              |             |             |             |            |
|              |             |             | Orcon       |            |
+--------------+-------------+-------------+-------------+------------+
| Cover/Light  | Aluminized  | STM0809-01  | Dunmore     | 800        |
| Block        | glass fiber |             |             | Dun-MET    |
|              | fabric      |             |             | Beta Cloth |
|              |             |             |             | (500F)/Al  |
+--------------+-------------+-------------+-------------+------------+
| Reflector    | Aluminized  | MDAC        | Dunmore     |            |
|              | PET two     | STM0691,    |             |            |
|              | sides       | type II,    | Sheldahl    |            |
|              |             | class 1,    |             |            |
|              | Aluminized  | grade A     | Orcon       |            |
|              | PET one     |             |             |            |
|              | side        |             |             |            |
+--------------+-------------+-------------+-------------+------------+
| Inner Layer  | Aluminized  | MDAC        | Dunmore     |            |
|              | reinforced  | STM0691,    |             |            |
|              | polyimide   | type II,    | Orcon       |            |
|              |             | class 2,    |             |            |
|              |             | grade B     |             |            |
+--------------+-------------+-------------+-------------+------------+
| Separator    | PET scrim   |             | Apex Mills  |            |
|              |             |             |             |            |
|              | Nomex scrim |             | Stern &     |            |
|              |             |             | Stern       |            |
|              |             |             |             |            |
|              |             |             | J. P.       |            |
|              |             |             | Stevens     |            |
+--------------+-------------+-------------+-------------+------------+

**Table 2: Typical MLI Joining Materials**

+----------------+-----------------+-----------------+----------------+
| **Layer**      | **Material**    | **Applicable    | **Suggested    |
|                |                 | Specs**         | Vendors**      |
+================+=================+=================+================+
| Exposed        | Fiberglass      | MIL-C-20079,    | Synthetic      |
| Threads        | coated with     | type III, class | Threads        |
|                | PTFE            | 6               |                |
+----------------+-----------------+-----------------+----------------+
| Non-exposed    | Nomex           | MIL-T-43636,    | Synthetic      |
| Threads        |                 | Type II, Size E | Threads        |
|                |                 |                 |                |
|                |                 |                 | Eddington      |
|                |                 |                 | Thread         |
+----------------+-----------------+-----------------+----------------+
| Adhesive       | 30 NF\*\*       |                 | 3M             |
+----------------+-----------------+-----------------+----------------+
| Tapes          | PSA Kapton tape |                 | 3M             |
|                |                 |                 |                |
|                | PSA aluminized  |                 |                |
|                | mylar tape      |                 |                |
+----------------+-----------------+-----------------+----------------+
| Lace           | PTFE Coated     |                 | W.F.Lake       |
|                | fiberglass      |                 |                |
|                | braided lacing  |                 |                |
|                | tape            |                 |                |
+----------------+-----------------+-----------------+----------------+

\*\*Use 30 NF in small amount as edge lock.

## MLI BLANKETS FABRICATION {#mli-blankets-fabrication .Style-Heading-2-+-Arial-12-pt}

After initial measurements and patterns of each MLI blanket are made, a
designer should review the design details and use the pattern to develop
a CAD model of the blanket and produce the fabrication drawings,
followed by installation drawings, and the final drawings. The following
steps are generally followed in MLI blanket fabrication.

**Steps in MLI Blanket fabrication**

1)  [Design]{.underline}: This includes taking measurements from
    existing hardware that will be covered by the blankets, and
    developing patterns for these blankets.

2)  [Fabrication of a Prototype Verification Unit (PVU)]{.underline}

3)  [Review MLI Design Details]{.underline}

4)  [MLI CAD Modeling]{.underline}

5)  [Evaluation and Modification of PVU]{.underline}

6)  [MLI Fabrication Drawings]{.underline}

7)  [Installed MLI Drawings]{.underline}

8)  [Final MLI Drawings]{.underline}

9)  [Fabrication of the Flight Units]{.underline}

10) [Package for Storage]{.underline}

# CLEAN ROOM

The MLI blanket panels should be fabricated in an ISO Class 8 clean room
or in an equivalent controlled area to reduce risk of contamination that
will affect the thermal performance of the blankets. Since the vacuum
deposited layer of metal on the reflector layers of MLI blankets is very
thin and fragile, it can easily be abraded. This is why the reflector
layers shall not be cleaned, and must be kept in the pristine condition
they were received from the manufacturer. The standard requirements for
an ISO Class 8 clean room are listed in Table 3

Table 3: Standard Requirements for an ISO Class 8 Clean Room

+-----------------------------------+----------------------------------+
| **Attribute**                     | **Requirement**                  |
+-----------------------------------+----------------------------------+
| Particle Count (\>0.5μm/ft3)      | ≤100,000                         |
+-----------------------------------+----------------------------------+
| Particle Monitoring               | Automatic counters               |
+-----------------------------------+----------------------------------+
| Air Conditioning                  | 22º C ±3º C (72° F ±5° F)        |
|                                   |                                  |
|                                   | 45% ±5% R. H.                    |
+-----------------------------------+----------------------------------+
| Air Filtration                    | Stages No. 1, 2, and 3           |
+-----------------------------------+----------------------------------+
| Pressure Differential             | Positive (higher P in clean      |
|                                   | room)                            |
+-----------------------------------+----------------------------------+
| Room Air Flow                     | 15-20 air changes/hour           |
+-----------------------------------+----------------------------------+
| Environmental Controls (T, RH)    | Located outside clean room       |
+-----------------------------------+----------------------------------+
| Airlocks                          | Required at all entrances        |
+-----------------------------------+----------------------------------+
| Garment Requirements              | Lint-free caps, hoods, gloves,   |
|                                   | booties                          |
+-----------------------------------+----------------------------------+
| Shoe Cleaner                      | Vacuum shoe cleaners             |
+-----------------------------------+----------------------------------+

# ATTACHMENT

MLI blankets must be designed to provide positive attachment to AMS-02
structure or to other blankets.

# DELIVERABLES

The following must be specified for delivery with the Class I (Flight)
MLI Blankets:

-   MLI CAD Models

-   Installed MLI Drawings

-   Certificate of Conformance

Blanket patterns and fabrication drawings may be retained by the
manufacturer, but must be made available to the end user upon request.