WFIRST-IC-SPEC-0067--1.pdf

Effective Date: July 2, 2019 Expiration Date: July 2, 2024

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National Aeronautics and Space Administration

Goddard Space Flight Center Greenbelt, Maryland

WFIRST-IC-SPEC-0067, Revision -

Wide Field Infrared Survey Telescope (WFIRST), Code 448

Process Requirement for

Adhesive Bonding

GSFC WFIRST CMO

July 8, 2019

Released https://ipdtdms.gsfc.nasa.gov/

WFIRST Process Requirements for Adhesive Bonding WFIRST-IC-SPEC-0067, Revision -ii

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Process Requirement for

Adhesive Bonding

Review/Signature/Approval Page

Prepared by:

Wes Alexander

Approving Signature Authority:

Chris Tolman

Electronic Approval available on-line at: https://ipdtdms.gsfc.nasa.gov iii

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Preface This document is a Wide Field Infrared Survey Telescope (WFIRST) Configuration Management (CM)-controlled document. Changes to this document require prior approval of the applicable Signature Authority or designee. Proposed changes shall be submitted to the WFIRST CM Office (CMO), along with supportive material justifying the proposed change.

In this document, a requirement is identified by “shall,” a good practice by “should,” permission by “may” or “can,” expectation by “will,” and descriptive material by “is.”

Questions or comments concerning this document should be addressed to:

WFIRST Configuration Management Office Mail Stop 448 Goddard Space Flight Center Greenbelt, Maryland 20771 iv

Change History Log

Revision Effective Date Description of Changes (Reference the Signature Authority Approval Date)

Revision - July 2, 2019 This was approved by the WFIRST Signature Authority via WFIRST-SCoRe-0162 on the effective date shown.

v

Table of TBDs/TBRs/TBSs [optional]

Item No. Location Summary Individual/ Organization

Actionee

Due Date

TBR1 2.6 Lap Shear Strength Requirement

WFIRST 11/19/2019

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Table of Contents

1 INTRODUCTION

1.1 Purpose

1.2 Scope

1.3 Related Documentation

1.3.1 Applicable Documents [and Forms]

1.3.2 Reference Documents

2 REQUIREMENTS

2.1 Material Requirements:

2.2 General Requirements:

2.2.1 Precautions:

2.2.2 Contamination Control Requirements

2.2.3 Facilities Requirements

2.2.4 Operator and Inspector Certifications

2.2.5 Material Handing and Packaging

2.2.6 Material Traceability and Identification

2.2.7 Process Qualifications

2.3 Process Requirements

2.3.1 General

2.3.2 Dry Fit

2.3.3 Composite Material Surface Preparation

2.3.3.1 Initial Cleaning

2.3.3.2 Abrasion

2.3.4 Use of Visual Standards

2.3.5 Final Cleaning

2.3.6 Tape Application for Adhesive Setback

2.3.7 Metallic Material Surface Preparation

2.3.8 Adhesive Mixing

2.3.9 Adhesive Application

2.3.10 Bondline Control

2.3.11 Work Time

2.3.12 Fixturing

2.3.13 Edge Coating

2.3.14 Cure Time

2.4 Workmanship Requirements

2.5 Fillets

2.6 Lap Shear Requirements

2.7 Adhesive Hardness Requirements

3 QUALITY ASSURANCE PROVISIONS AND TESTING METHODS

3.1 General

3.2 Traceability

3.3 Visual Inspection

3.4 Non-Destructive Inspection

3.5 Adhesive Hardness Inspection

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3.6 Lap Shear Strength

3.7 Rejection

4 PREPARATION FOR DELIVERY

4.1 Certification of Test

4.2 Identification

4.3 Package and Storage

APPENDIX A ABBREVIATIONS AND ACRONYMS

List of Tables Table 1. Adhesive Cure Time Requirements

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1 INTRODUCTION

1.1 Purpose

The purpose of this document is to identify the adhesive bonding process used on the Instrument Carrier for the Wide Field Infrared Survey Telescope The contractor is responsible for the all requirements within this specification (WFIRST-IC-SPEC-0067).

1.2 Scope

This specification describes the requirements and sets limits of acceptance for adhesive bonding of composite materials, metallic details and assembled structures for the Instrument Carrier (IC) for the NASA Goddard Space Flight Center (GSFC) WFIRST Mission.

1.3 Related Documentation

The latest versions of all documents below should be used. WFIRST documents can be obtained from URL: https://ipdtdms.gsfc.nasa.gov.

1.3.1 Applicable Documents [and Forms]

The following documents are referenced within this document and are directly applicable or contain policies or other directive matters that are binding for the contents of this document. In the event of conflict between an Applicable Document and the content of this document, the applicable Signature Authority has the final authority for conflict resolution.

In case of conflicting requirements between the requirements of this specification and those noted on the engineering drawing, the requirements of the drawing shall govern.

Document Number Title WFIRST-IC-SPEC-0017 Material Specification, 954-6 Preimpregnated Tape WFIRST-IC-SPEC-0062 Specification for Application of BR127 Primer for WFIRST WFIRST IC-SPEC-0032 WFIRST Non-Destructive Examination Specification and Defect-

Acceptance Criteria for Non-Metallics ASTM-D-1002 Standard Test Method for Apparent Shear Strength of Single

Lap Joint Adhesively bonded Metal Specimens by Tension Loading

ASTM-A-313 Standard Specifications for Stainless Steel Spring Wire SAE-AMS4954 Titanium Alloy Welding Wire, 6AL4V ASTM A580 Standard Specification for Stainless Steel Wire IEST-STD-CC1246E Product Cleanliness Levels and Contamination Control

Program WFIRST-SYS-PLAN-0051 WFIRST Contamination Control Plan (CCP)

1.3.2 Reference Documents

The following documents are referenced herein and amplify or clarify the information presented in this document. These documents are not binding on the content of this document.

Document Number Title

NONE

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2 REQUIREMENTS

This section defines the functional and performance requirements for the WFIRST Process requirement for Adhesive Bonding as defined in Section 3.1.

2.1 Material Requirements:

Material to be bonded shall be, at a minimum, visually inspected prior to bonding operations and shall have no defects or other features which would interfere with the proper bonding. Surface preparation for bonding of metallic parts (aluminum, invar, or titanium) shall be per WFIRST-

IC-SPEC-0062.

2.2 General Requirements:

2.2.1 Precautions:

Abrasion of carbon composites will generate dust particles.

Vacuum systems shall be used for debris removal following any abrasion operations and during operations as needed to control debris. Vacuum systems shall be equipped with micro filters capable of filtering particles 20 microns or larger.

Personal protective equipment to be used during abrasion shall include gloves and dust mask or respirator.

2.2.2 Contamination Control Requirements

Abrasion operations inherently generate debris. To the extent possible, debris shall be removed during the operation as the debris is generated. Care shall be taken to ensure that debris from abrasion does not contaminate adjacent hardware, particularly in situations where it would be difficult to remove debris from such areas. In such cases, areas adjacent to the areas being abraded shall be covered or masked using non-contaminating material to prevent intrusion of debris. All parts delivered to GSFC shall be cleanable to a level 300A per IEST-STD-CC1246E.

Extreme care shall be exercised to avoid the possible introduction of contamination into materials, prepared surfaces, or into the equipment used.

Non-contaminating lint-free wipes shall be used for cleaning. The specific types used shall be approved by the GSFC Materials Engineering Branch (MEB).

Nitrile or polyethylene gloves shall be used with isopropyl alcohol, but only polyethylene gloves shall be used with acetone. Acetone dissolves many gloves and will leave residue.

Flashbreaker tapes shall be of the non-contaminating, silicone free adhesive type.

All expendable materials which are used in operations involving the flight materials or with materials that will contact the flight materials shall be reviewed and approved by the GSFC MEB prior to use.

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When parts, particularly cleaned parts, are left for an extended period of time they shall be covered with a non-contaminating material.

2.2.3 Facilities Requirements

Bonding operations shall be performed in a controlled, visibly clean area. There shall be no evidence of organic contaminants, particularly oils, greases, or silicones in the area. Mold release agents in uncured form are not permitted in bonding areas. Areas where mold release agents are used shall be physically isolated from bonding areas. The area ventilation system shall be operating such that it does not draw in contaminants from other areas, such as airborne oils, silicones, mold release agents and exhaust fumes. The area shall be monitored for a) particulate content, using a particle counter or other suitable method, and b) organic contaminates, using a witness mirror or suitable method.

2.2.4 Operator and Inspector Certifications

Operators performing bonding operations and inspectors reviewing such operations shall be certified by a GSFC approved training program which includes bonding procedures, surface preparation and material handling operations. This training may be a training program defined by the Contractor, but shall be approved by GSFC. The training shall be used to qualify each individual working on the WFIRST program. It will include bonding of representative samples of each hardware configuration, with results verified by testing. There shall be a controlled list of the operators who have been qualified to perform adhesive bonding in accordance with this specification.

2.2.5 Material Handing and Packaging

Material shall be protected from handling damage at all times. Laminates shall be wrapped in protective material, such as non-contaminating plastic film or acid-free Kraft paper, during storage. Laminates and other parts shall be well supported and shall not be stacked unless previously wrapped or covered in protective material. Laminated materials shall be transported using appropriate non-contaminating backing materials to prevent bending and cracking during transport. Acceptable methods include cardboard wrapped in aluminized Mylar or other non-contaminating film. After cleaning, contact with surfaces shall be with gloves or non-contaminating packaging material.

2.2.6 Material Traceability and Identification

Laminates and other composite parts shall be labeled with permanent ink to maintain traceability to the original raw material and cure process.

If surface preparation will remove identification marking, the marking shall be transferred to an adjacent area of the material unless otherwise specified by the engineering drawing.

2.2.7 Process Qualifications

Prior to use on flight hardware, the bonding process for each hardware configuration shall be qualified. All processes shall have demonstrated sufficient controls to ensure reproducible performance. Qualification shall consist of either a) fabrication of development test specimens which represent the flight configuration, or b) process development specimens which represent the bonding configuration to a sufficient extent that the effectiveness of the bonding process is proven. The GSFC MEB shall review and approve the process qualification for all bonded joint

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configurations for flight hardware prior to the bonding of flight hardware. Readiness for performing flight operations shall be documented and presented via a Process Readiness Review.

Process readiness shall include demonstration of consistent performance including documentation, tooling, facilities, and operator and inspector training.

2.3 Process Requirements

2.3.1 General

Proper preparation of surfaces is critical to achieve proper bonding. Every effort must be taken to ensure proper preparation of the surfaces and to prevent contamination of prepared surfaces prior to mating of surfaces.

2.3.2 Dry Fit

Parts to be bonded shall be dry fit prior to adhesive application to ensure that they can be properly mated and to achieve the desired bondline. In cases where bondline thickness is critical, such as clips etc., dry fit should be performed after abrasion and shall be followed by final cleaning.

2.3.3 Composite Material Surface Preparation

The following procedure applies to laminates cured from unidirectional or fabric pre-impregnated tape per WFIRST-IC-SPEC-0017.

Surface preparation shall be performed over an area at least 0.1” greater in any direction than the dimension of the mated part to be bonded. It is recommended that the area to be bonded be masked as required with non-contaminating, non-silicone adhesive tape, flashbreaker tape, or equivalent non-contaminating material.

Surface preparation of carbon fiber composites shall consist, as a minimum, of the following steps:

a) Cleaning with acetone, followed by isopropyl alcohol wipe

b) Abrasion

c) Cleaning with isopropyl alcohol

The part shall be adequately secured during surface preparation.

2.3.3.1 Initial Cleaning

Thoroughly clean bonding surfaces using acetone (reagent grade or better). Polyethylene gloves shall be worn while using acetone. Wipe in one direction, parallel to the fibers if possible. Do not use a circular or “back and forth” motion, as this only moves the contaminants around on the surface. Perform second wipe using isopropyl alcohol (reagent grade or better). Nitrile or polyethylene gloves shall be worn while using isopropyl alcohol. Wipe in one direction, parallel to the fibers if possible. Do not use a circular or “back and forth” motion, as this only moves the contaminants around on the surface. Allow to dry for 15 minutes minimum prior to abrasion.

2.3.3.2 Abrasion

Abrasion shall be performed, un-lubricated, with one of the following:

a) Scotchbrite 7447 (red)

b) Aluminum oxide paper, 180 to 220 grit, lubricant free

Use of silicon carbide abrasive paper is not permitted unless specifically approved by the MEB, as it can contain lubricants that will interfere with proper bonding.

Abrasion shall be performed in the direction of the fibers, particularly for unidirectional material.

M55J unidirectional tape is susceptible to damage by overly aggressive abrasion. T300 surfaces are more resistant to abrasion and require a higher degree of abrasion to achieve a suitable surface for bonding.

The intent of the abrasion is to break the surface glaze of the resin without penetrating significantly into the fibers. The surface should have a dull, matte finish after abrasion. In all cases, the abrasion should not break fibers, which is evidenced by substantial amounts of black carbon in the abrasion dust.

Isopropyl alcohol (reagent grade or better) shall be used to remove abrasion debris.

2.3.4 Use of Visual Standards

Areas prepared for bonding should be visually inspected against a standard to insure that all areas have been properly abraded. The visual standards shall represent satisfactort, inadequate and excessive abrasion conditions. Visual standards representing all of the configurations to be bonded (M55J, T300, tubes, plates, etc.) shall be prepared by the Contractor and reviewed and approved by the GFSC MEB representative.

2.3.5 Final Cleaning

Wipe thoroughly using isopropyl alcohol (reagent grade or better). Nitrile or polyethylene gloves shall be worn while using isopropyl alcohol. Wipe in one direction, parallel to the fibers if possible. Do not use a circular or “back and forth” motion, as this only moves the contaminants around on the surface.

Allow to dry for 30 minutes minimum prior to application of adhesive. Areas exposed for more than 8 hours must be re-cleaned by wiping with isopropyl alcohol. For areas that are inaccessible after dry fit e.g the inside of a tube where a fitting is bonded, this re-cleaning requirement does not apply as long as the parts are covered after final cleaning.

After final cleaning, contact with the prepared bonding surfaces shall be minimized. Contact with cleaned surfaces is only permissible with gloved hands. If contaminating contact occurs, surface shall be re-cleaned as described above before bonding occurs.

2.3.6 Tape Application for Adhesive Setback

When specified on engineering drawings, Polytetrafluoroethylene (PTFE) tape shall be applied to composite parts to achieve adhesive setback. The engineering drawing shall specify the location and dimensions of the taped off area.

Apply the tape as follows:

a) Prepare the surface to be taped using the same method as a surface to be bonded.

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b) Place 1” wide Permacel P-430 PTFE tape in the locations specified on the drawing.

c) Fold over any excess tape onto itself to prevent it from adhering to any cut edges of tubes.

d) Ensure the tape is smooth, without bubbles or creases.

e) After application of adhesive, completely clean out the fillet at the edge of the tape.

f) Once cured, the excess tape may be trimmed . Any trimming must be done so as to prevent damage to the parts.

2.3.7 Metallic Material Surface Preparation

Unless otherwise specified by engineering drawing, metallic parts to be bonded shall be primed with BR127 primer per WFIRST-IC-SPEC-0062. This includes titanium, invar, and aluminum parts.

Primer surfaces shall be thoroughly wiped with isopropyl alcohol (reagent grade or better) prior to bonding. Nitrile or polyethylene gloves shall be worn while using isopropyl alcohol. Wipe in one direction. Do not use a circular or “back and forth” motion, as this only moves the contaminants around on the surface.

Allow to dry for 15 minutes minimum prior to application of adhesive. Areas exposed for more than 8 hours must be re-cleaned by wiping with isopropyl alcohol.

After final cleaning, contact with the prepared bonding surfaces shall be minimized. Contact with cleaned surfaces is only permissible with gloved hands. If contaminating contact occurs, surface shall be re-cleaned before bonding occurs.

2.3.8 Adhesive Mixing

All adhesive shall be within the manufacturer’s shelf life prior to use. The adhesive shall be mixed per the manufacturer’s data sheet unless otherwise specified by engineering drawing.

Extreme care shall be exercised to avoid contamination of the adhesive material. When mixing adhesive, the use of wooden utensils is not acceptable.

When the use of Cab-O-Sil™ is specified for the adhesive mix, it shall be dried at 125 to 130°C for a minimum of 48 hours immediately before use. This is normally done in a shallow stainless steel or Pyrex glass tray to provide maximum surface exposure for removing water. Keep the Cab-O-Sil™ covered loosely with aluminum foil at the recommended temperature.

A mix record and hardness sample shall be prepared for each adhesive mix used. The mix record shall include as a minimum, the weights of all ingredients and any processes that affect the adhesive properties. The mix record shall be clearly traceable to the adhesive vendor lot number and to the parts being bonded. Quality Assurance shall review all mix records to insure all information is documented. The hardness sample shall be a representative specimen of the material mixed including the degassing step. The sample shall be of sufficient size to result in a valid hardness measurement, typically a casting in a “hockey puck” dish, minimum .25 inch thick. The hardness sample shall be cured concurrently with the part, including any post cure.

The hardness sample shall be clearly marked for traceability to the mix record.

All adhesive mixtures shall be vacuum degassed at 22 inches of Hg minimum for a minimum of 5 minutes. Avoid excessive time in vacuum which may boil-off volatile components of adhesive mixtures.

2.3.9 Adhesive Application

The mixed adhesive shall be applied to both surfaces to be bonded using a technique that will produce the desired bondline thickness as specified on the engineering drawing. In order to avoid loss of bond strength from open time exposure, a maximum of 25 minutes of elapsed time (“work time”) is allowed between application of adhesive to the parts and the mating of the parts.

Alignment and clamping of parts shall be performed using fixtures as required. Care shall be taken to ensure pre-stressing the bond joint or adherends shall be avoided

2.3.10 Bondline Control

Bondline control method shall be specified on the engineering drawing. Unless otherwise specified, the bondline thickness may be controlled by one of the following methods:

a) Solid glass microspheres, 0.005” to 0.020” diameter, 0.3 to 0.5% by weight of adhesive mixture.

b) Bond wire, stainless steel per ASTM-A580 or ASTM-A-313 or titanium per AMS4954, 0.005” to 0.020”.

c) Diameter, or other bond wire approved by the MEB.

d) Features integral to the parts being bonded.

e) Shims only if approved by GSFC.

f) Nickel spheres for grounding only if approved per location by GSFC.

*Note that microspheres are typically not effective in controlling bondline in situations where parts will scrape against each other during mating of parts, such as insertion of tubes into fittings.

In such cases, the use of bond wires is required.

Materials used for bondline control, including microspheres and bond wire, shall be traceable to the manufacturer certification data.

2.3.11 Work Time

The work time is defined as the maximum time permitted between the start of adhesive mix and the final mate and adjustment of bonded parts. If the parts cannot be properly mated or adjusted before the work time expires, the parts shall be demated, cleaned and the surfaces prepared as described in Section 2.3.3 prior to bonding.

2.3.12 Fixturing

The fixturing method shall be sufficient to assure that the relative position of the bonded parts is maintained within the engineering drawing tolerances.

2.3.13 Edge Coating

Edge coating of composite parts shall be performed per engineering drawings where necessary to ensure edge defects do not propagate and to reduce fiber pulls. EA 9396 is the preferred adhesive, but alternate adhesives may be used after approval of GSFC. The edge coating

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adhesive shall be mixed per Section 2.3.8. Post application visual examination will include verification of even coating of all machined surfaces with no drips or runs. The edge coating shall not interfere with the bonding surface.

All edge coating shall be cured at room temperature for a minimum of 8 hours followed by oven curing at 70°C for 2 hours minimum.

2.3.14 Cure Time

Full adhesive cure time at room temperature after mixing is defined in Table 2.1

Table 1. Adhesive Cure Time Requirements

Material Cure time EA 9309.2 NA 5 Days EA 9396 5 Days

Adhesives and cure times not listed in Table 2.1 must be approved by GSFC. Bonded joints shall be cured for 24 hours minimum before any operations that could significantly load the joint, though bonded joints may be handled after 16 hours.

For 9309.2 NA adhesive, a post cure of 70ºC ± 2.5ºC for a minimum of 8 hours is required. The ramp rate for heating shall be 0.15ºC per minute maximum. The ramp rate for cooling shall be 3ºC per minute maximum.

An alternative post cure is as follows:

a) Ramp at 2.0ºC perminute maximum to 42 ± 2.5ºC; hold for 2 hours minimum.

b) Ramp at 0.15ºC perminute maximum to 70 ± 2.5ºC; hold for 8 hrs. minimum. Then ramp down at 3 ºC per minute maximum to 28 ºC.

Additional cure times and post curing instructions may be identified on engineering drawings.

2.4 Workmanship Requirements

2.5 Fillets

Bonded fittings and other parts shall meet adhesive fillet radius requirements as specified on the engineering drawing.. There shall be no excess adhesive that would interfere with mating of parts or installation of hardware at higher levels of assembly. There shall be no excess adhesive on adjacent surfaces or in areas other than the bonded joint(s). Fillet rework is not allowed unless approved by GSFC.

2.6 Lap Shear Requirements

Lap shear specimens are required for surface preparation process verification for all bonded joint configurations. A set of quantity 5 minimum lap shear samples consistent with specimen dimensions in ASTM D 1002 will be prepared for each configuration. The sample materials shall fully represent the parts being bonded. This includes the surface preparation of metallic parts using BR127 primer, which shall be prepared at the same time as the flight hardware parts.

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These samples shall be prepared using the same processing and operators as the hardware being represented. The bondline used for the test specimens shall be 0.010” ± 0.005”. The specimens shall be cured using the same cure as the joints being represented, including post cure if applicable.

Lap shear sample testing is required for each purchased material lot of adhesive.

The lap shear strength shall be a minimum of (TBR1) psi at room temperature.

2.7 Adhesive Hardness Requirements

The minimum hardness shall be 74 Shore D for 9309.2 NA and 75 Shore D for EA9396.

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3 QUALITY ASSURANCE PROVISIONS AND TESTING METHODS

3.1 General

Unless otherwise required by the engineering drawing or statement of work, the fabricator shall be responsible for the performance of qualification and acceptance tests as defined herein. The fabricator shall be responsible for maintaining traceability of all materials used in the test specimens, parts and assemblies.

3.2 Traceability

Materials and process history are required with each part furnished to this specification. This shall include, but is not limited to, the following:

a) Identification of composite laminates and metallic parts.

b) Identification of adhesive used, including traceability number.

c) Vendor certification and acceptance test results (if required) on adhesive lot.

d) Process parameters, including dates, cure times, temperatures, and bond area temperature and humidity data.

3.3 Visual Inspection

Bonded joints shall be visually inspected after the full cure to ensure the following:

a) No visual voids or bubbles.

b) No visual particulate contamination, such as dirt, dust or hair.

c) No evidence of adhesive bond separation after curing.

d) Complete filleting if required.

e) No undercuts in bonds.

Inspection shall be performed by trained personnel.

3.4 Non-Destructive Inspection

N-Destructive Inspection shall be performed on all bonded joints unless otherwise specified per WFIRST IC-SPEC-0032 spec type III or IV.

3.5 Adhesive Hardness Inspection

Adhesive sample hardness shall be measured by a Shore-D-scale durometer, which is within calibration limits. Mix records shall be inspected for completeness and to confirm full completion of cure.

3.6 Lap Shear Strength

Lap shear test specimens shall be prepared and tested per ASTM D 1002. To the extent possible, the tested configuration shall represent as closely as possible the materials being represented.

The cross head speed shall be 0.05 in/min. Shims shall be used to ensure applied load is applied through the centerline of the specimen.

3.7 Rejection

Failure of a bonded assembly to comply with all of the requirements specified in Section 3 shall be cause for rejection of the hardware.

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4 PREPARATION FOR DELIVERY

4.1 Certification of Test

The fabricator shall provide a certificate of tests made to determine conformance to the requirements of this specification. The certificate and other data submitted shall show evidence of the fabricator’s designation, the drawing and serial number of the bonded assembly(s) or part(s) such that the certificate and data report may be identified with the shipment.

4.2 Identification

The drawing and serial numbers of the bonded assembly(s) or part(s) shall be indicated on each assembly or part and container. This marking will be used to track all fabricated parts. The fabricator can use standard in-house methods to mark parts if not identified on engineering drawings.

4.3 Package and Storage

Bonded assemblies shall be handled, transported and stored in such a manner that they shall remain capable of meeting the requirements of this specification. Assemblies or parts shall be provided with protective covering at all times except as necessary for inspection or fabrication processes. Assemblies and parts shall be transported and stored in a protective container and shall only be removed from the container as necessary for inspection or fabrication processes.

Bonded assemblies and parts shall be suitably packaged to prevent any contamination or damage in transport or storage.

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Appendix A Abbreviations and Acronyms

Abbreviation/ Acronym

DEFINITION

GSFC Goddard Space Flight Center MEB Materials Engineering Branch TBD To Be Determined TBR To Be Revised TBS To Be Scheduled