80JSC018R0008_-_GVNVI_RFP_-_Statement_of_Work.docx

Statement of Work

Gulfstream V Nadir Viewport Installation

Flight Operations Directorate Aircraft Operations Division

National Aeronautics and Space Administration Lyndon B. Johnson Space Center

Gulfstream V Nadir Viewport Installation

Houston, Texas 77058

Contents

1.0 Scope

The National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC) plans to install two nadir (down) looking optical viewports in its Gulfstream GV, S/N 672. See Figure 11. These viewports will be used to support a wide variety of airborne science programs. This statement of work defines the scope of work necessary to structurally modify the aircraft to install the viewports and relocate existing aircraft systems such as control cables, electrical wiring, and hydraulic lines to provide clearance for the viewport installation. Repairs (Minor/Major) and Alterations (modifications) shall meet Federal Aviation Administration (FAA) Code of Federal Regulation (CFR) 14 certification.

Figure 11: NASA GV, S/N 672

2.0 Requirements Definition

The following definitions differentiate between requirements and other statements contained in this statement of work:

3.0 Reference Documents

The documents shown in Table 31 are referenced in this statement of work.

Table 31: Reference Documents

4.0 General Requirements

4.1 Project Management

The Contractor shall provide project management support for the work accomplished under this statement of work such as schedule, cost, and technical supervision.

4.2 Project Status Reports

The Contractor shall provide weekly project status reports via teleconference. The status reports shall cover important project tasks (e.g. design, fabrication, aircraft modification) and shall include a running list of actions items and action item status (e.g. action item tracking spreadsheet).

4.3 Contract Surveillance

NASA reserves the right to conduct surveillance inspections at the Contractor’s facility at any time during the contract period to ensure compliance with contract requirements. The Contractor shall support these surveillance activities as required.

4.4 Program Management Reviews

The Contractor shall conduct program management reviews as follows:

a) For the Baseline Contract (see Section 5.0), conduct all program management reviews identified in Table 41.

b) For contract Options 1 and 2 (see Sections 6.1 and 6.2), conduct the program management reviews identified in Table 41, Items 4.4.1 thru 4.4.4 and Item 4.4.8.

c) Provide an agenda, presentation charts, and a schedule update with percent completion of tasks at each review. (Preliminary presentation materials shall be provided to NASA no later than 3 business days prior to each review)

d) If requested by NASA, provide computer aided design models, analysis models, or other data prior to reviews.

e) Following all reviews, provide meeting minutes with action items up through and including the Critical Design Review.

Table 41: Program Management Reviews

Review project schedule.

Contractor location

Review analysis plan.

Review draft verification & validation plan.

Review procurement, fabrication, & modification plan Review project schedule.

Ellington Field

Review design, drawings, analysis, etc.

Review preliminary verification & validation plan.

Review procurement, fabrication, & modification plan Review project schedule.

Reference AOD 33820.

Contractor location

Review design, drawings, analysis, etc.

Review final verification & validation plan.

Review procurement, fabrication, & modification plan Review project schedule.

Reference AOD 33820.

Ellington Field

Reference AOD 33843.

Contractor location

Reference AOD 33820.

via teleconference

Reference AOD 33840 & AOD 33843.

Contractor location

5.0 Baseline Contract[footnoteRef:1] [1: Note: Requirements associated with seat track installation, floor modifications, and antenna relocations noted in NASA Request for Information Solicitation Number: 80JSC017GVDIV will be completed by NASA prior to the aircraft being delivered to the Contractor for modification.]

The Contractor shall provide all engineering, fabrication, and installation support for all tasks in Section 5.0.

5.1 Nadir Viewport Installation

5.1.1 Optical Viewport Installation Location

The Contractor shall structurally modify the aircraft to install two nadir (down-looking) circular viewports with 17.4-inch minimum diameter clear apertures centered at approximate fuselage stations F.S. 290.50 and F.S. 339.50. See Figure 51.

Figure 51: Viewport Locations (approximate)

5.1.2 Optical Window Pack Interface

5.1.2.1 Interface

The Contractor shall design the viewports to interface with the Government furnished optical window pack assembly shown on reference drawings 25-0000054, Optical Window Pack Installation, and 25-0000055, Optical Window Pack Assembly. The Contractor shall assume an optical window pack assembly weight of 90 pounds maximum.

5.1.2.2 Ease of Installation

The Contractor shall design the optical window pack interface for ease of installation of the window pack assembly identified in Section 5.1.2.1. The Contractor shall design the viewport window pack interface to allow the window pack assembly to:

a) Be installed by two (2) technicians in less than two (2) hours

b) Be removed by two (2) technicians in less than two (2) hours

c) Be installed or removed with aircraft weight on wheels and not require any aircraft shoring

5.1.3 Optical Viewport Structural Design

The Contractor shall:

a) Design the optical window pack structural interface to significantly limit the transfer of undesirable stresses (e.g. bending stresses) to the NASA provided optical window pack assembly identified in Section 5.1.2 and the optical windows installed in the window pack. The Contractor shall demonstrate that glass windows installed in the NASA provided window pack assembly will have a stress that does not exceed 1000 psi.[footnoteRef:2] [2: The 1000 psi stress value is preliminary. NASA will provide a final not to exceed stress for the glass window material after contract award.]

b) Develop an integrated stress analysis model that includes the NASA provided window pack assembly.[footnoteRef:3] [3: NASA will provide a window pack assembly with both a single and double pane window configuration. ]

c) Demonstrate that metallic portions of the NASA provided window pack assembly will have positive margins of safety with a Factor of Safety equal to 2.0.

d) Consider all loading sources (e.g. static, pressure, aerodynamic, vibration, temperature) and all aircraft operating conditions (e.g. ground, maneuver, landing, emergency) when analyzing aircraft structural modifications.

e) Design the window pack structural interface to accommodate required seal surfaces for the NASA provided optical window pack.

5.1.4 Optical Viewport Pressure Plug

The Contractor shall supply three (3) aluminum viewport pressure plugs for the optical viewports.[footnoteRef:4] The viewport pressure plugs will be installed when the aircraft is flown in an FAA certificated configuration. [4: One (1) pressure plug is a spare.]

5.1.5 Optical Viewport Aerodynamic Drag

The Contractor shall design the viewport installation using best aviation practices (e.g. minimal changes to aircraft outer mold line, blended fairing) to minimize aerodynamic drag when either the optical window pack assembly (see Section 5.1.2) or viewport pressure plug (see Section 5.1.4) are installed.

5.2 Aircraft System Relocation

5.2.1 General[footnoteRef:5] [5: NASA will relocate the aircraft antennas shown on NASA AOD drawing 25-0000074, Layout, Antennas – Science Modification. Cover plates will be installed at the old antenna locations. ]

The Contractor shall relocate all necessary aircraft systems to provide clearance for the two optical viewports identified in Section 5.1. The aircraft systems shall be relocated to provide a clear and unobstructed 17.4 inch minimum diameter aperture for payloads mounted on the cabin floor. See Figure 52 thru Figure 54. The relocated aircraft systems shall also provide adequate clearance to easily install and remove both the window pack assembly identified in Section 5.1.2 and optical viewport pressure plug identified in Section 5.1.4.

Example aircraft systems that may need to be relocated include but are not limited to:

1. Oxygen Lines & Oxygen Bottles

2. Hydraulic Lines

3. Environmental Control System (ECS) Relocation

4. Wire harnesses

5. Total Air Temperature Probe Line

Note: The gust lock and speed brake cables shown in Figure 53 do not need to be relocated by the Contractor.

17.4

CLEAR

APERTURE

(minimum) Experiment

SEAT

TRACK

QTY: 4 ROWS

Fuselage Cross Section

NADIR

VIEWPORT

Figure 52: Viewport Clear Aperture

Speed brake cables

Gust lock cables

Forward lavatory dump tube to be permanently removed by NASA

F.S. 315.5

F.S. 392.5

F.S. 273.5

Figure 53: NASA GV, S/N 672, Interior w/Floor Boards Removed

Figure 54: NASA GV, S/N 672, Exterior

5.3 Aircraft Structural Life Limit

The Contractor shall provide a written report demonstrating that all aircraft modifications do not negatively impact the Original Equipment Manufacturer’s (OEM’s) aircraft structural life limit.

5.4 Aircraft Operations and Maintenance[footnoteRef:6] [6: If the Contractor implements a phased modification approach, the Contractor shall satisfy these requirements following the completion of each modification phase.]

The Contractor shall design all aircraft modifications to accommodate and not negatively impact:

a) Normal flight operations for all phases of flight

b) OEM specified in-flight routine or contingency procedures (e.g. emergency oxygen bottle gauge inspection)

c) OEM specified maintenance procedures (e.g. oxygen system servicing)

5.5 Verification & Validation

5.5.1 Verification & Validation Plan

The Contractor shall provide a written verification & validation plan for all Section 5.0 requirements and conduct all verification and validation activities. The verification plan shall include a matrix describing the type of verification activity to be used for each requirement (e.g. analysis, demonstration, inspection, test) and shall include all verification and validation activities required for FAA certification. The verification and validation plan shall be approved by NASA prior to verification and validation activities.

5.5.2 Verification & Validation Report

The Contractor shall provide a written report documenting all verification and validation results.

5.6 Analysis

The Contractor shall perform all required analyses, (e.g. structural, aero, damage tolerance) required to satisfy NASA and FAA airworthiness requirements. The Contractor shall:

a) Document and review analysis plan with NASA prior to analysis start. Analysis plan shall include modeling approach, loads, safety factors, fasteners analysis method, analysis verification process, etc.

b) Deliver formal written reports documenting the analyses.

c) Obtain completed Federal Aviation Administration (FAA) Form 8110’s prior to any major aircraft modifications/alterations. See Section 5.13.

5.7 Quality Management System

The Contractor shall have a quality management system that is compliant with the requirements of the current Society of Automotive Engineers (SAE) AS9100, Quality Management Systems - Requirements for Aviation, Space, and Defense Organizations.

5.8 Fabrication & Aircraft Modification

5.8.1 General

The Contractor shall:

a) Perform aircraft modification/maintenance activities in accordance with applicable aircraft OEM technical data.

b) Follow standard recommended aviation practice and workmanship standards (e.g. FAA, Aerospace Industries Association, Society of Automotive Engineers Aerospace Standards) for all aircraft modifications (e.g. wire harness fabrication, tube fabrication, part marking, wire marking, electrical terminal crimping, electrical bonding/grounding, cable/tube clamping, heat treating).

5.8.2 Labor, Tooling, and Materials

The Contractor shall provide all labor, tooling, and materials to perform all modification activities identified in Section 5.0.

5.8.3 Hangar Facility

The Contractor shall provide a hangar facility large enough to fully contain NASA’s GV aircraft and hangar the aircraft for all aircraft modification activities identified in Section 5.0.

5.8.4 Shoring Plan

The Contractor shall develop a written aircraft shoring plan that demonstrates how fuselage dimensions and other critical aircraft features will be dimensionally monitored during the modification to prevent aircraft damage.

5.8.5 Aircraft Corrosion Protection and Painting

The Contractor shall apply appropriate aircraft corrosion protection finishes, sealants, primer, and paint (interior and exterior) for all aircraft modifications including any required touch-up finishing/paint.

5.8.6 Weight and Balance

The Contractor shall complete an aircraft weight and balance in accordance with the Gulfstream-V maintenance manual.

5.8.7 Foreign Object Debris (FOD) Program

The Contractor shall maintain a foreign object debris program for all aircraft modification work to ensure removal of all foreign objects that could impact safe aircraft operations.

5.8.8 Procurement

The Contractor shall:

a) Procure materials and hardware that are new and unused.

b) Provide Manufacturer’s Test Reports (MTRs) for all raw materials (e.g. chemical analysis composition, mechanical properties testing, heat treat strip charts).

c) Provide certificates of conformance for all hardware and third party processes.

d) Ensure that counterfeit materials and hardware are not purchased for, or installed on, NASA aircraft.

5.8.9 Independent Material Testing

The Contractor shall:

a) Provide independent material testing for raw materials used to fabricate safety critical components (e.g., failure of a component could result in a catastrophic hazard such as critical damage to an aircraft or injury to personnel). The testing shall be performed after all critical material treatments/processes have been completed (e.g. following heat treat).

b) Deliver material test reports to NASA following testing. The test reports shall clearly identify the part number of the associated component.

c) Deliver the as-tested material coupons to NASA. The coupons shall be bagged and tagged for traceability (e.g. include associated part number).

5.8.10 Deviations

The Contractor shall obtain written approval from NASA for any deviations from approved drawings or technical data that are beyond those allowed by the aircraft OEM.

5.9 Ground & Flight Testing[footnoteRef:7] [7: Any fixtures fabricated for testing, such as window plugs, will be considered a contract deliverable.]

5.9.1 Ground Testing

The Contractor shall prepare written ground test plans and perform ground testing as required to verify design requirements and aircraft modifications (e.g. ground pressure test).[footnoteRef:8] The written test plans shall be approved by NASA prior to test start. In particular, the test program shall include instrumented tests to verify the optical viewport structural design requirements listed in Section 5.1.3. The Contractor shall document the results of all tests in a written report. Reference AOD 33840, Flight Readiness Review and Test Readiness Review and AOD 33843, Flight Test. [8: NASA will supply pilots and aircraft fuel to operate the aircraft during ground and flight testing.]

5.9.2 Flight Testing

The Contractor shall prepare written flight test plans as required to verify design requirements and aircraft modifications (e.g. functional test flight). The written test plans shall be approved by NASA prior to test start. In particular, the test program shall include instrumented tests to verify the optical viewport structural design requirements listed in Section 5.1.3. The Contractor shall document the results of all tests in a written report. The Contractor shall support flight testing as required. Reference AOD 33840, Flight Readiness Review and Test Readiness Review and AOD 33843, Flight Test.

5.10 As-Built Drawing Package

The Contractor shall provide a complete drawing package (piece part, assembly, component removal, and installation) containing all drawings required for the modification (mechanical, electrical, etc.) The drawing package shall document the as-built configuration, i.e. all redlines shall be incorporated. The drawings shall include all information necessary to fabricate and install the components such as dimensions, electrical schematics, tube bend tables, tube/cable clamp locations, rivet/bolt hole locations, fastener torques, notes, bill of materials, etc. The drawings shall also include all special process and procedure notes such as material finishing, electrical bonding, oxygen service cleanliness requirements, etc. The Contractor shall deliver to NASA any referenced process specifications that are not easily obtained by NASA in the open market. The Contractor shall deliver all drawings in either AutoCAD DXF/DWG format (preferred) or Adobe vector PDF (i.e. not bitmap) and all 3D CAD models in native and STEP format.

5.11 Operation & Maintenance Manual Change Pages

The Contractor shall provide change pages to the aircraft operation and maintenance manuals (including Illustrated Parts Catalog) for all aircraft structures or systems affected by the modification. The change pages shall include inspection requirements for continued airworthiness related to the modifications.

5.12 NASA Airworthiness Review

The Contractor shall support NASA’s airworthiness review process to approve the aircraft for flight. Reference AOD 33820, Engineering Projects. All data required for FAA certification shall be submitted to NASA for review (e.g. all required FAA Form 8110 documents shall be signed by an FAA Designated Engineering Representative (DER) prior to the NASA Airworthiness Review). NASA may approve the aircraft for flight as a public use aircraft prior to official FAA certification.

5.13 Federal Aviation Administration (FAA) Certification Package The Contractor shall ensure all Repairs (Minor/Major) and Alterations (modifications) meet Federal Aviation Administration (FAA) Code of Federal Regulation (CFR) 14 certification requirements. The FAA certificated configuration will be with the aluminum viewport pressure plugs described in Section 5.1.4 installed.[footnoteRef:9] At a minimum, the certification package shall include the following: [9: NASA will operate the aircraft as a “public aircraft” for other viewport configurations such as with optical glass windows installed.]

a) Aircraft Logbook entry for return to service

b) Completed FAA Form 337’s for all repairs and alterations

i) Completed FAA Form 8110’s for all repairs and alterations

ii) Inspection for Continued Airworthiness (ICA) requirements

5.14 Final Data Package

The Contractor shall deliver an electronic data package containing all data generated/required for the modification. All documents shall be legible and complete. The Contractor shall provide the Government with an unlimited rights license to use the data. Examples include but are not limited to:

1. Design

a. Computer Aided Design (CAD) models in native and STEP format

b. Finite element models in native format (Nastran bulk data files preferred)

c. As-built drawing package (see Section 5.10)

2. Reports

a. Structural analysis reports

b. Structural life limit report

c. Verification & Validation Plan/Report

d. Damage Tolerance Analysis (DTA) reports

e. Test plans and reports

f. Instructions for Continued Airworthiness (as required/needed)

3. Procurement & Fabrication

a. Material test reports / certifications

b. Certificates of Conformance

c. Test coupons

d. Specification sheets for commercial-off-the-shelf items that are not MS, AN, NAS, NASM components

e. Quality review documentation

f. Weight & Balance report

4. FAA Certification Package

5.15 NASA Aircraft Inspection & Maintenance

The Contractor shall allow NASA civil servant and/or NASA contractor personnel to perform aircraft inspection and maintenance actions at the Contractor’s facility should they be required for vendor surveillance or to keep the aircraft flight worthy during the modification period.

6.0 Contract Options

The Government may exercise the options outlined in Sections 6.1 and 6.2.

6.1 Option 1: Viewport Shutter Design[footnoteRef:10] [10: This option is for design only, i.e. does not include fabrication.]

6.1.1 General

The Contractor shall design an electrically activated viewport shutter to protect the exterior side of window glass in both viewports from being damaged, particularly from debris ejected from the nose gear during takeoff and landing. The design of the shutter shall consider failure of a glass optical window(s) installed in the viewports without further damage to the aircraft due to the shutter installation.

6.1.2 Operation

The Contractor shall design the shutter to open or close throughout the entire aircraft operating envelope. The shutter shall be designed to:

a) Fully open in less than 90 seconds

b) Fully close in less than 90 seconds

6.1.3 Clear Aperture

The Contractor shall design the shutter to provide a clear and unobstructed 17.4 inch minimum diameter aperture for payloads mounted on the cabin floor when fully opened. See Figure 52.

6.1.4 Easily Removable Design

The Contractor shall design the shutter assembly to be easily removable for maintenance activities or for aircraft missions where reduced aerodynamic drag is required. The Contractor shall design the shutter assembly to allow the assembly to:

a) Be installed by two (2) technicians in less than two (2) hours

b) Be removed by two (2) technicians in less than two (2) hours

c) Be installed or removed with aircraft weight on wheels and not require any aircraft shoring

6.1.5 Electrical Control

The Contractor shall provide an electrical interface for shutter position, power, and control. The electrical interface shall be accessible from the pressurized interior of the aircraft.

The electrical interface shall consist of the following interfaces:

a) Input power

b) Forward shutter OPEN command discrete input

c) Forward shutter CLOSE command discrete input

d) Forward shutter locked OPEN discrete output

e) Forward shutter locked CLOSED discrete output

f) Aft shutter OPEN command discrete input

g) Aft shutter CLOSE command discrete input

h) Aft shutter locked OPEN discrete output

i) Aft shutter locked CLOSED discrete output

Power and signal formats/levels are negotiable. NASA AOD engineering to approve format selections prior to detailed design.

6.1.6 Shutter Aerodynamic Drag

The shutter installation shall minimize aerodynamic drag in both open and closed positions.

6.1.7 Shutter Failure Modes

The Contractor shall design the shutter so that failure of the shutter mechanism does not impact normal or safe flight operations (e.g. takeoff, flight, landing).[footnoteRef:11] [11: For example, if the shutter fails during flight in a partially open or closed position, this configuration shall not impact normal or safe flight operations. The shutter will be repaired after landing.]

6.1.8 Analysis

The Contractor shall analyze the shutter design per Section 5.6.

6.1.9 Installation & Operation Instructions

The Contractor shall provide all necessary written installation and operations instructions.

6.1.10 Drawing and Data Package

The Contractor shall provide a drawing and data package per Section 5.10 and Section 5.14 requirements (minus fabrication data).

6.1.11 Airworthiness Certification

The Contractor shall provide the appropriate certification package (stress analysis, aerodynamic analysis, etc.) for NASA airworthiness certification. The Contractor shall meet the requirements of Section 5.13, Federal Aviation Administration (FAA) Certification Package, for any permanent aircraft modifications that are flown in the FAA certificated configuration (e.g. viewport mounting hard-points, electrical pass-throughs).[footnoteRef:12] [12: NASA will operate the aircraft as a “public aircraft” with the viewport shutter installed.]

6.2 Option 2: Optical Viewport Window Defog System Design[footnoteRef:13] [13: This option is for design only, i.e. does not include fabrication.]

6.2.1 General

The Contractor shall design a hot air window defog system for both optical viewports to keep optical windows defogged during all flight phases and altitudes.

6.2.2 Safety Thermal Shutoff

The Contractor shall design the heater to have a safety thermal shutoff. The heater shall not exceed the rated max temperature when input power is applied to the electrical interface.

6.2.3 Electrical Control

The Contractor shall provide electrical interfaces for defog system control. The interfaces shall allow independent defog system control for each viewport. The electrical interface shall be accessible from the pressurized interior of the aircraft.

The electrical interface shall consist of the following interfaces:

a) Blower input power

b) Heater input power

Power and signal formats/levels are negotiable. NASA AOD engineering to approve format selections prior to detailed design.

6.2.4 Analysis

The Contractor shall analyze the window defog system design per Section 5.6.

6.2.5 Installation & Operation Instructions

The Contractor shall provide all necessary written installation and operations instructions.

6.2.6 Drawing and Data Package

The Contractor shall provide a drawing and data package per Section 5.10 and Section 5.14 requirements (minus fabrication data).

6.2.7 Airworthiness Certification[footnoteRef:14] [14: NASA will operate the aircraft in both FAA certificated and “public aircraft” configurations with the defog system installed.]

The Contractor shall provide the appropriate certification package (e.g. drawings, stress analysis) for NASA Airworthiness certification. The Contractor shall meet the requirements of Section 5.13, Federal Aviation Administration (FAA) Certification Package, for any permanent aircraft modifications that are flown in the FAA certificated configuration (e.g. aircraft wiring).

7.0 Contract Type

The Gulfstream V Nadir Viewport Installation (GVNVI) contract will consist of two Contract Line Item Numbers (CLINs), as detailed below.

7.1 Firm-Fixed Price (FFP) Baseline

CLIN 1 is for FFP baseline work, including options if applicable. The contract baseline includes all work related to the installation of the nadir viewport windows, as detailed in the Statement of Work.

7.2 Time-and-Materials (T&M) Task Orders

CLIN 2 is for potential T&M task orders. The Contractor shall work any Government-directed T&M requirements via Government issued time and material task orders. T&M task orders may be issued to account for unknown aircraft maintenance actions or other Government-directed changes such as engineering design, engineering analysis, fabrication, or other unknown aircraft modification tasks that result during the performance of this nadir viewport installation contract. All T&M task orders shall be approved by the Government Contracting Officer prior to commencement of any work by the Contractor.

7.2.1 Contractor Furnished Items

Materials shall to be provided by the Contractor when essential to the task order requirements. Title to all property purchased by the Contractor for which the Contractor is entitled to be reimbursed as a direct item of cost under this contract or individual task orders shall pass to and vest in the Government upon the vendor’s delivery of such property to the Contractor or in accordance with FAR 52.245-1(e)(3). The Contractor is required to obtain written authorization from the Contracting Officer’s Representative (COR) prior to procuring any items where the individual item procurement costs exceed $3,500 and in accordance with NASA FAR Supplement 1852.245-70 (Aug 2015) Contractor Requests for Government-Provided Equipment. Note: Written authorization from the CO or the COR is not required for property that was reviewed and approved as part of an issued task order. All property acquired by the Contractor and meeting the requirements of Government property for the use or ownership of the Federal government, become the property of the Federal Government and subject to FAR 52.245-1. The Contractor shall document the transfer of Government property to the Government as directed by the Contracting Officer.

8.0 Government Furnished Data or Equipment

The Government will furnish the items shown in Table 81.

Table 81: Government Furnished Data or Equipment

9.0 Place of Performance

The Contractor shall perform all work specified in this contract at the Contractor’s site including all aircraft modification work and ground and flight testing. If NASA determines that Contractor performance at the Government’s site is required, work will be performed at Johnson Space Center (JSC), Ellington Field located in Houston, Texas, or other NASA operating location that may be determined following contract award.

10.0 Travel

The Contractor shall travel to Ellington Field in Houston, TX for the reviews outlined in Section 4.4. Additionally, based on aircraft availability and at the Contractors discretion, the Contractor may travel to Ellington Field for on-aircraft inspections during periods when the aircraft is not at the Contractor’s facility.

11.0 Shipping

Drawings and data shall be delivered in electronic format either via email or mailed to:

NASA Johnson Space Center Bldg. 265, Ellington Field Houston, TX 77034

12.0 Schedule

To be incorporated at contract award.

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