80AFRC24R0008-Statement of Work.pdf

STATEMENT OF WORK

GULFSTREAM-IV NEXT GENERATION AIRBORNE SYNTHETIC

APERTURE RADAR (AirSAR-NG) MODIFICATION

DATE: 7 DECEMBER 2023

National Aeronautics and Space Agency Armstrong Flight Research Center Edwards, California

TABLE OF CONTENTS

1.0 BACKGROUND

2.0 OBJECTIVES AND SCOPE

3.0 BASIC CONTRACT DELIVERABLE

4.0 OPTIONAL CONTRACT DELIVERABLES

5.0 OVER AND ABOVE COSTS

6.0 PERIOD OF PERFORMANCE

7.0 AIRCRAFT DESCRIPTION

8.0 SYSTEM REQUIREMENTS

8.1 Modification Structural and Design Standards

8.2 Aircraft Performance

8.3 Instrument Canoe Requirements

8.4 Instrument Blister Requirements

8.5 Instrument Calibration Requirements

8.6 Ground Support Equipment

9.0 QUALITY ASSURANCE REQUIREMENTS

10.0 OTHER REQUIREMENTS

11.0 DEPOT MAINTENANCE INSPECTION REQUIREMENTS (CONTRACT OPTION)

12.0 AIRCRAFT NADIR VIEWPORTS (CONTRACT OPTION)

APPENDIX 1 – NASA CONCEPTUAL DESIGN PACKAGE

APPENDIX 2 – NASA AIRCRAFT SAFETY OF FLIGHT GUIDELINES (AFG-7123-001)

APPENDIX 3 – NASA LIFTING STANDARD (NASA-STD-8719.9)

1.0 BACKGROUND

For several years, NASA’s Unmanned Air Vehicle Synthetic Aperture Radar (UAVSAR) developed and operated by NASA has been employed on multiple NASA Gulfstream Platforms.

Currently, the UAVSAR instrument utilizes a large external centerline pod to house radar components and antennas. To support future Earth Science missions, NASA is developing the Next Generation AirSAR (AirSAR-NG) instrument to replace/upgrade the existing UAVSAR instrument and extend the capabilities of NASA’s SAR platforms.

2.0 OBJECTIVES and SCOPE

The objective of the AirSAR-NG project is to provide a more capable, versatile, and maintainable AirSAR platform. To meet this objective, the UAVSAR instrument is being redesigned and replaced. The new design will enable more hardware to be housed in the aircraft cabin. Three SAR antennas will be mounted on the aircraft fuselage in new conformal enclosures, eliminating need for an external pod.

This requirement is to design, fabricate, and install a fuselage blister and ventral canoe on a NASA Gulfstream-IV aircraft. The aircraft is a former US Navy G-IV with a cargo door (T/N N522NA, SN1199) currently located at Langley Research Center. No permanent structural modifications (other than the cargo door) have been made to the aircraft. All performance flight testing will be planned and conducted by NASA. This is a designated Special Use aircraft and NASA will be responsible for Airworthiness Certification.

A conceptual design of the aircraft modification is provided below. For additional details, see Appendix 1.

Contractor will be responsible for obtaining any required information from Gulfstream for the completion of this requirement.

3.0 BASIC CONTRACT DELIVERABLE (CLIN 0001)

The contractor shall provide a complete modification design package including all software CAD and FEM models, drawings, and structural analysis reports, including loads, stress, modal and aerodynamic analysis, and a full technical data package, for NASA approval. The requirements of a proper analysis reports are defined in section 5 of AFG-7123.1-001, included in Appendix 2, and referenced in DRD-3. Additionally, NASA has provided a conceptual design in Appendix 1.

The contractor shall participate in a series of Technical Interchange Meetings (TIM) with NASA to enable the contractor to refine the proposed aircraft modification until modification design is delivered and approved.

4.0 OPTIONAL CONTRACT DELIVERABLES.

4.1 Ventral Canoe Modification (CLIN 0002). Following NASA approval of the modification design package (CLIN 0001), the contractor shall fabricate and install the ventral canoe per approved design. Specific Canoe Enclosure Requirements are included in Section 8.3 below.

4.2 Fuselage Blister Modification (CLIN 0003). Following NASA approval of the modification design package (CLIN 0001), contractor shall fabricate and install the fuselage blister enclosure per approved design. Specific Blister Enclosure Requirements are included in Section 8.4 below.

4.3 Ground Support Equipment (CLIN 0004). Design and provide unique Ground Support Equipment (GSE) and associated procedures to remove/reinstall ventral canoe and radar systems. Provide design drawings and “proof load certification” documents and procedures for conducting subsequent load tests. Specific requirements are included in Section 8.6.

4.4 Depot Maintenance Inspection (CLIN 0005). Provide a depot maintenance inspection on the G-IV per Gulfstream maintenance manual; 8C check (96 month) in conjunction with basic aircraft modification (Additional information and requirements listed in Section 11.0 below). No aircraft engine maintenance is required.

5.0 OVER and ABOVE COSTS

NASA will authorize what is commonly termed “over and above” work for associated modification, inspection and maintenance and repair work that would not be included within the work included in Section 3.0 and Section 4 (if options are exercised). All ODCs shall be associated with performance and within the scope of the requirement. Costs are allowable to the extent they are reasonable, allocable, and determined to be allowable under FAR Part 31. All ODCs must be approved by the Contracting Officer or his/her authorized representative prior to the purchase of supplies or performance of services.

6.0 PERIOD OF PERFORMANCE

The anticipated schedule for contract deliverables is summarized below. Within 15 days after contract award, the contractor shall provide an updated schedule to demonstrate their ability to meet following period of performance actions. After that, the Contractor shall provide updates to the schedule on a weekly basis. Reference DRD-1, DRD-2, and DRD-3.

CLIN 0001 START TECHNICAL

INTERCHANGE MEETING(S)

10 days after contract award

CLIN 0001 COMPLETE NASA-

APPROVED MOD DESIGN

PACKAGE

120 days after contract award.

NASA to notify contractor when the mod design package is approved.

(Optional CLINs 0002-0006) NASA WILL DELIVER

AIRCRAFT TO MOD

FACILITY WITHIN 45 DAYS

AFTER COMPLETION OF

NASA-APPROVED DESIGN

PACKAGE

(Optional CLINs 0002-0006) COMPLETE MODIFICATION 150 days after aircraft delivery to modification facility

(Optional CLINs 0002-0006) COMPLETE AIRCRAFT

MAINTENANCE

150 days after aircraft delivery to modification facility

7.0 AIRCRAFT DESCRIPTION

The aircraft is a US Navy G-IV with a cargo door (T/N N522NA, S/N 1199) currently located at NASA’s Langley Research Center. No permanent structural modifications other than the cargo door have been made to the aircraft.

8.0 SYSTEM REQUIREMENTS

8.1 Modification Structural and Design Standards. Structural components of the existing airframe shall conform to FAR 25 (14 CFR, Part 25), Subpart C, except as noted below. Design and construction shall conform to FAR 25 (14 CFR, Part 25), Subpart D.

Airframe should be analyzed to the entire flight envelope. If any reductions are needed in order to meet structural margin requirement, notify NASA for concurrence.

The Contractor shall document all proof tests in formal written reports.

8.0 SYSTEM REQUIREMENTS (CONT)

8.2 Aircraft Performance.

REQ# Name Requirement Rationale/Notes

8.2.1 Platform

Range/Duration

The AIRSAR-NG Platform shall have a flight range of 3400* miles or greater when fully configured to carry the AIRSAR-NG instrument (3 simultaneous radar configuration) throughout the entire G-IV flight envelope.

Needed to meet science mission goals for deployment flexibility and cost.

8.2.2 Max Operating

Altitude

The AIRSAR-NG Platform shall have a maximum operating altitude of FL450 (45,000 feet)*.

Needed to meet science mission goals for deployment flexibility and cost.

8.2.3 Controllability

with Shockwaves

Shockwaves shall not degrade basic HQ and trim capability.

To ensure this is within the G-IV Mach trim capability (assuming this is the same as the G-III).

8.2.4 Lateral-

Directional Stability

The modifications to the aircraft shall not reduce crosswind limits for takeoff and landing, increase single-engine Minimum Controllable Airspeed (VMC), or cause Dutch Roll that exceeds the capability of the aircraft's Yaw Damper.

Needed to ensure the basic airworthiness of the aircraft.

8.2.5 Operation Ground

Speed

The AIRSAR-NG shall be capable of collecting science data over a range of ground speeds from 85 m/s to 250 m/s while cruising at FL410 with a 140 kts headwind or tailwind component.

Needed to ensure the aircraft can remain within ground speed limits required for radar system spatial resolution when experiencing high winds aloft.

8.2.6 Yaw Damper Off

limitations

No changes to yaw damper off limitations.

Needed to ensure the basic airworthiness of the aircraft.

8.2.7 Structural

Modification Weight

The weight of the structural modifications to the aircraft shall not exceed the following limits:

- Instrument Blister: 125lbs

- Instrument Canoe: 770lbs

- Ventral Fin: 40lbs

Needed to ensure adequate mass budget remains to install Radar and Mission Systems equipment in the aircraft cabin without exceeding zero fuel gross weight limits.

8.2.8 Aerodynamic Stall No appreciable changes to the stall

characteristics of the wing.

Avoid recalculating TOLD data and recalibrating AoA systems.

8.2.9 AoA Errors

No appreciable changes to the flow around the AoA sensors.

To avoid recalibration of the stick shaker and pusher systems.

8.2.10 TOLD (takeoff

and landing data)

No appreciable changes to takeoff and landing data due to increased drag, aerodynamic, or pitot-static errors.

Avoid recalculating TOLD data and recalibrating AoA systems.

8.2.11 Panel Flutter

Fairings or blanking plates design shall not result in panel flutter issues throughout the G-IV envelope.

Flat panels associated with this canoe/blister design could cause flutter issues.

8.2.12 Airflow changes

around engines

Avoid any airflow stagnation issues around the engines due to canoe/blister.

Avoid potential compressor stall issues associated with the engines.

8.2.13 Flow disturbance on antennas aft of the blister/canoe

Any turbulent flow shall not cause fatigue vibration on antennas aft of the canoe/blister.

Identify early any potential issues and either eliminate turbulent airflow or support antennas with increase strength (doublers).

*Note: No modifications to the aircraft are planned to enhance aircraft performance. Since the Gulfstream G-IV is the predetermined platform, the requirements for service level, range and duration are performance objectives (not thresholds). The goal is to retain G-IV performance as much as practical to support science mission objectives.

8.3 Instrument Canoe Requirements.

REQ # Name Requirement Rationale

8.3.1 Instrument Canoe Mass

The AIRSAR-NG Platform shall provide an instrument Canoe that can support two Radar Systems weighing up to 500lbs each. (Not including canoe structure mass)

Note: Each Radar System includes one each:

- Digital Front End (DFE) Chassis

- Antenna

- Power Distribution Unit (PDU)

- Inertial Navigation Unit (INU)

- Cabling

Required to support mass of canoe with two radar system modules.

8.3.2 Instrument Canoe

Electrical Interfaces

The AIRSAR-NG Platform shall provide electrical, data, signal connection feedthroughs between In- Cabin Instruments and Canoe Instruments.

Required to provide power to Canoe Instruments.

8.3.3 Instrument Canoe Internal

Mounting

The AIRSAR-NG Platform Instrument Canoe shall provide internal mounting accommodations for each Radar System (Antenna, PDU, DFE Electronics, and INU) such that each Radar System (Fore/Aft) can be installed and removed from the Instrument Canoe as a unit without assembly or disassembly of the Radar System.

Required to securely mount instrument components in Canoe.

8.3.4 Instrument Canoe Antenna

Viewing Angle (45 degrees)

The AIRSAR-NG Platform instrument Canoe shall integrate two left-side-viewing (at 45° to nadir) antennae each with dimensions at least 25 in x 70 in x

8.5 in. Antennae must be able to be removed from the canoe structure and will contain its own radome.

Required to angle antenna at optimal position for radar mission data collection in flight.

8.3.5 Instrument Canoe Thermal

Control

The AIRSAR-NG Platform / Instrument Canoe shall be capable of independently controlling the cooling supplied to the forward and aft radar systems in the Instrument Canoe.

Ensures payloads with differing thermal requirements can be kept within their respective operational temperature ranges.

8.3.6 Instrument Canoe Thermal

Control Requirements

(OPERATIONAL)

The Radar Canoe electronics must maintain an operational temperature range of -40 C to 45 C in air and on ground.

Maintains hardware components within operational temperature ranges.

8.3.7 Instrument Canoe Thermal

Control Requirements

(NON-OPERATIONAL)

The Radar Canoe electronics must maintain a non-operational temperature range of -50 C to 70 C.

Maintains hardware components within non-operational temperature ranges.

8.3.8 Instrument Canoe Thermal

Heat Dissipation

(OPERATIONAL)

The AIRSAR-NG Platform shall be capable of dissipating 2000 Watts of heat from each Canoe Instrument Module.

Maintains hardware components within operational temperature ranges.

8.3.9 Instrument Accessibility

The AIRSAR-NG Canoe shall be designed to enable installation, test, maintenance, and inspection of the radar systems while mounted (electrically and mechanically) to the aircraft.

Allows for easy maintenance and repair if problems occur.

8.3.10 Instrument Canoe Blank-

Off Covers

Blank-off covers will be provided to complete the OML of the aircraft when one or both antenna assemblies are not installed in the canoe and when canoe is removed.

Required for airworthiness when blister antenna is no installed.

8.3.11 Instrument Canoe

Structure

The bulk of the Instrument Canoe structure must be removeable from the aircraft such that the aircraft may be operated without the Instrument Canoe installed.

Required for use of the aircraft in a passenger or utility configuration.

8.3.12 Instrument Canoe

Structure

The Instrument Canoe shall not interfere with any basic equipment or functions of the aircraft. Any of the basic aircraft equipment that interferes with the Instrument Canoe installation (i.e. radio antennas, lights, drains, fueling receptacles, etc.) shall be relocated elsewhere on the aircraft such that their intended functionality is retained.

Retains basic functionality of the aircraft.

8.3.13 Instrument Canoe Ground

Clearance

The instrument canoe shall maintain worst-case ground clearance greater than three inches per MIL-STD-1289D 4.3.5.C

Required to support deployed operations.

8.3.14 Instrument Module Fuel

Intrusion

The Instrument Canoe shall prevent intrusion of fuel into the Radar Systems.

Required for reliability of the Radar System.

8.3.15 Instrument Canoe Antenna

Pitch Angle

The AIRSAR-NG Canoe shall position the antenna such that the angle between the longitudinal axis of the antenna and the flight path vector of the aircraft is minimized when the aircraft is cruising between Mach 0.67 and 0.85 at FL410 for gross weights between 50,500 lbs and 69,000 lbs.

Required to keep antenna parallel to the ground for radar mission data collection in flight.

8.4 Instrument Blister Requirements.

REQ# Name Requirement Rationale

8.4.1 Instrument

Blister Mass

The AIRSAR-NG Platform shall provide an instrument Blister capable of supporting an instrument mass of 200 lbs. (not including blister structure mass).

Required to support mass of blister when housing either Ka or P-Band antenna components are installed.

8.4.2

Instrument Blister Electrical Interfaces

The AIRSAR-NG Platform shall provide electrical, data, signal connection feedthroughs between In-Cabin Instruments and Blister Instruments.

Required to provide power to Blister Instruments.

8.4.3 Instrument Blister Antenna Viewing Angle

The AIRSAR-NG Platform instrument Blister shall integrate an external, left-side-viewing (at 45° to nadir) antenna with dimensions at least 25 in x 70 in x 8.5 in a removable section of the blister wall with its own integrated radome.

Required to angle antenna at optimal position for radar mission data collection in flight.

8.4.4 Instrument Blister Thermal Requirements

(OPERATIONAL)

The Blister electronics must maintain an operational temperature range of -40 C to 45 C in air and on ground.

Maintains hardware components within operational temperature ranges.

8.4.5

Instrument Blister Thermal Requirements

(NON-

OPERATIONAL)

The Blister electronics must maintain a non-operational temperature range of -50 C to 70 C.

Maintains hardware components within non-operational temperature ranges.

8.4.6 Instrument

Accessibility

The AIRSAR-NG Blister shall be designed to enable installation, test, maintenance, and inspection while mounted (electrically and mechanically) to the aircraft.

Allows for easy maintenance and repair if problems occur.

8.4.7 Instrument Blister Blank- Off Cover

A blank-off cover will be provided to complete the OML of the aircraft when an antenna assembly is not installed.

Required for airworthiness when blister antenna is not installed.

8.4.8 Instrument Blister Outer Mold Line

The design and installation of the Instrument Blister shall not interfere with basic aircraft functions or require recalibration of the basic aircraft’s air data system.

Required for airworthiness when the Blister is installed.

8.4.9 Instrument Blister Antenna Pitch Angle

The AIRSAR-NG Blister shall position the antenna such that the angle between the longitudinal axis of the antenna and the flight path vector of the aircraft is minimized when the aircraft is cruising between Mach 0.67 and 0.85 at FL410 for gross weights between 50,500 lbs and 69,000 lbs.

Required to keep antenna parallel to the ground for radar mission data collection in flight.

8.5 Instrument Calibration Requirements. The modification design must facilitate the following measurements.

REQ# Name Requirement Rationale

8.5.1 Antenna

Calibration

The AIRSAR-NG Platform shall allow for the survey of the position of the GNSS antennas, INUs, and radar antennae (canoe/blister) in aircraft reference coordinates to an accuracy of 1 mm.

Accurate measurement of the lever arms between the Radar, GPS, and INUs will simplify instrument calibration.

8.5.2 Antenna

Separation During Use

The AIRSAR-NG Platform shall maintain the separation of the GNSS antennas, INUs, and radar antennae (canoe/blister) in aircraft reference coordinates to an accuracy of 5 mm during in-flight and on ground data takes.

Limiting change in the lever arms between the Radar, GPS, and INUs during flight will simplify instrument calibration.

8.5.3

Orientation Survey of

Radar Antenna and

INU

The AIRSAR-NG Platform shall allow for the survey of the orientation of the radar antenna and INUs in aircraft reference coordinates to an accuracy of 2 milliradians.

Accurate pre-flight knowledge of the radar and GPS antennas in the INUs reference frame will simplify instrument calibration.

8.5.4

Blister and Canoe Radar Antenna and

INU

Orientations

The AIRSAR-NG Platform shall maintain the blister and canoe radar antenna and INUs reference frame orientations at cruise conditions to a stability of 0.2 milliradians.

Rigidity between radar antenna and INUs mounting fixtures simplifies instrument calibration.

8.5.5

Blister and Canoe

Mounting Tolerances

The AIRSAR-NG Platform shall have mounting tolerances for the blister and canoe radar antenna and blister mounted INUs to an accuracy of 0.2 milliradians.

Provides proper INUs reference coordinates repeatable between successive installation.

8.5.6 Inspection

Monument

The AIRSAR-NG Platform shall provide an inspection monument within 48 inches of the Blister Antenna and Forward Instrument Canoe Antenna that establishes the longitudinal, lateral, and vertical axes of the aircraft reference coordinate system.

Needed to facilitate accurate and timely survey of the radar and mission system components.

8.6 Ground Support Equipment.

REQ# Name Requirement Rationale

8.6.1 GSE Design Standard

GSE shall be designed in accordance with SAE

ARP1247E.

Common commercial Aerospace GSE design standard.

8.6.2 GSE Lifting Equipment

Design Standards

GSE that performs a lifting function shall be designed in accordance with ASME B.30 and NASA-STD-8719.9.

NASA lifting device requirements.

8.6.3 Canoe Instrument GSE

The following GSE items shall be provided:

1. Canoe Instrument Test & Transportation Cart

2. Canoe Instrument Test & Transportation Cart Covers

3. Canoe Instrument Upload Device

GSE Items Required to support preliminary

CONOPS.

8.6.4 Canoe Instrument Test & Transportation Cart Load Capacity

The Canoe Instrument Test & Transportation Cart shall be capable of supporting the weight of the Canoe Module (Radar System and any inseparable Canoe structure).

Needed to store and transport the Radar System.

8.6.5 Canoe Test & Transportation

Cart Size

The length of the container shall not exceed 12 feet, and width shall not exceed 6 feet.

Need to be able to transport two canoe radar modules, the blister antenna, cabin electronics hardware, cabling, and any associated GSE in a standard 53-foot semi-trailer.

8.6.6 Canoe Transportation

Container Door Clearance

The Canoe Instrument Test & Transportation Cart shall fit through a 72in wide by 84in high doorway while supporting the Canoe Module.

Needed to ensure the Radar System can be transported between buildings at the Lab.

8.6.7 Canoe Instrument Prep

Frame Maximum Height

The Canoe Test & Transportation Cart shall be capable of mounting the Canoe Module such that the

The radar electronics should be mounted at a reasonable working height when in the electronics are at a working height between 3 feet and 4 feet above the floor.

frame for integration and test of the instrument.

8.6.8 Canoe Instrument Prep Frame / Canoe Upload Device Compatibility

The Canoe Test & Transportation Cart shall have sufficient clearance to allow the Canoe Instrument Upload Device to install and remove the Canoe Module from the Transportation Cart.

Needed to ensure the Upload Device can install and remove the Module from the Transportation Cart.

8.6.9 Canoe Instrument Test & Transportation Cart Modularity

The Canoe Instrument Test & Transportation Cart and Canoe Instrument Upload Device shall be compatible with either the forward or aft canoe module regardless of module configuration.

Needed to minimize number of GSE items required to handle Canoe Modules.

8.6.10 Canoe Instrument Test &

Transportation Cart Access

The Canoe Instrument Test & Transportation Cart shall allow sufficient access to the Radar System (antennas and electronics) while the Canoe Module is supported on the Cart to allow assembly/disassembly of the electronics and testing of the assembled Radar System.

Needed to integrate and test the Radar System.

8.6.11 Canoe Test & Transportation

Cart Mobility

The Canoe Instrument Test & Transportation Cart shall be supported using castering wheels with brakes.

Needed to transport the Radar System with a minimum of custom or specialized equipment.

8.6.12 Canoe Transportation

Container Loading and Unloading

The Canoe Instrument Test & Transportation Cart shall be fork-liftable along its long and short axes with the Canoe Module installed.

Needed to transport the Radar System.

8.6.13 Canoe Transportation

Container Tiedowns

The Canoe Instrument Test & Transportation Cart shall be equipped with tiedown points capable of securing it to the interior of a 53-foot Semi trailer for transportation.

Needed to transport the Radar System.

8.6.14 Canoe Instrument Upload

Device Crane Lift Elimination

The Canoe Instrument Upload Device shall be capable of installing and removing the Canoe Module from the Canoe Instrument Test & Transportation Cart without the use of a crane.

Needed to upload the Radar System to the aircraft.

8.6.15 Canoe Instrument Upload

Device

The Canoe Instrument Upload Device shall be capable of transporting the Canoe Module between the Cart and the aircraft in a ramp or hangar environment.

Needed to upload the Radar System to the aircraft.

8.6.16 Canoe Instrument Upload

Device

The Canoe Instrument Upload Device shall be capable of lifting and aligning the Canoe Module to the Canoe frame for repeated uploading and downloading of the Canoe Module from the aircraft.

Needed to upload the Radar System to the aircraft.

9.0 QUALITY ASSURANCE REQUIREMENTS

9.1 Certified Quality Management System. The Contractor shall provide and maintain either a AS9110C or AS9100D certified Quality Management System. The Contractor’s inspection program shall ensure compliance with technical guidance, engineering specifications, and EASA/FAA regulations applicable to aircraft modification, repair, and maintenance.

Documentation shall be required for traceability, accountability, and a historical record of design, testing, inspection, qualification, and acceptance of all materials and components.

9.2 Quality System. The Contractor shall possess current FAA Repair Station certification to 14 C.F.R. Part 145 and AS9110 or AS9100 third-party certification.

9.3 Suppliers. The Contractor shall be responsible for Quality Assurance of vendors, suppliers, and subcontractors providing services under this contract to verify compliance with accepted standards. For those vendors who provide EASA/FAA certified parts and services, a copy of the valid certification shall be made available to NASA.

9.4 Non-conformance. The Contractor shall have in place a procedure for reporting of nonconforming articles, materials, and equipment. (“Non-conformance” is defined as a condition of any article, material, or service in which one or more characteristics do not conform to the specified requirements. This includes failures, discrepancies, deficiencies, defects, anomalies, and malfunctions).

9.5 Inspection. The Contractor shall provide inspectors to verify that work is performed in accordance with technical specifications and the documentation is completed in accordance with the Gulfstream-IV Maintenance Manual.

9.6 Tool Control. NASA requires the Contractor to utilize a system of positive tool control, including (but not limited to) shadowing of toolboxes. Contractors not in compliance with this requirement shall propose an alternative method of tool control.

9.7 Metrology. The Contractor shall have an acceptable metrology recall system in-place to ensure that all tools requiring calibration are current and in good working condition.

9.8 Government Source Inspection. All work performed on this contract shall be subject to inspection by the Government, NASA, or NASA designated personnel at any time. Government designated inspectors will provide follow up inspections to work performed on the aircraft, as designated on the work cards. These NASA inspectors will be designated in writing by the Contracting Officer as the Contracting Officer’s Representative (COR).

9.9 Quality Manual. The Contractor shall utilize a Quality Manual for use on this contract.

9.10 Documentation. Documentation and records of all non-routine (O&A) repairs shall be included along with the completed work cards. Documentation shall include signature sign-off and inspection compliance.

9.11 Warranties. The Contractor shall submit, and recover whenever possible, warranty claims for the Government for parts and labor. The Contractor shall maintain internal records of the warranty program, which shall be available for review by Government personnel. The Contractor shall pass through to the Government any supplier warranties acquired by the Contractor as a result of work performed under this contract.

9.12 Government Mandated Inspection Points (GMIPs). Following NASA’s approval of the aircraft modification design, GMIPs will be defined and coordinated with contractor to allow government to inspect specific aspects of the maintenance and modification.

10.0 OTHER REQUIREMENTS

10.1 NASA Access During Modification/Maintenance Activities. The Contractor shall permit NASA Technical staff to have access to the aircraft, on a non-interference basis, during the Modification/maintenance activities. This requirement allows NASA technical staff to complete minor non-contract tasks as needed.

11.0 DEPOT MAINTENANCE INSPECTION REQUIREMENTS (CONTRACT

OPTION)

Depot maintenance inspection is required within the planned schedule for the aircraft modification. To minimize overall schedule, NASA may exercise this option in conjunction with the aircraft modification.

11.1 Period of Performance. Provide a depot maintenance inspection on the G-IV per Gulfstream maintenance manual; 8C check (96 month) in conjunction with basic aircraft modification. If this contract option is exercised, the work shall be completed within same period of performance as Aircraft Modification schedule.

11.2 Work Cards. The contractor shall perform inspections and maintenance strictly in accordance with inspection Work Cards. The effort shall include all labor, tooling, and materials necessary to complete all inspections, repairs, stripping, cleaning, and painting, and return the aircraft to service in accordance with applicable FAA certification standards.

11.3 Engineering. The Contractor shall utilize an FAA DER (designated engineering representative) to design and approve any deviations from manufacturer’s fabrication and repair specifications during the O&A portion of the maintenance.