Slideshows

GSFC Clean Room

List View »

The red object is known as a "hat," which shields PACE’s Earth coverage antenna and prevents emission of radiation during testing.

Time-lapse video of installing the Bus Star Tracker Sensor (STS) on the -Z Panel of the PACE spacecraft at NASA Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

The red object is known as a "hat," which shields PACE’s Earth coverage antenna and prevents emission of radiation during testing. Credit: Henry, Dennis (Denny)

Time-lapse video of PACE Tilt mechanism moving inside the Thermal Vacuum chamber at NASA Goddard Space Center. Credit: Henry, Dennis (Denny)

Transporting HARP2 polarimter to thermal vacuum chamber. Credit: Mellos, Katherine

HARP2 polarimeter installed in chamber for pre-thermal testing. Credit: Mellos, Katherine

Preparing HARP2 polarimeter for thermal vaccum testing. Credit: Mellos, Katherine

Installating HARP2 polarimeter on thermal vacuum plate. Credit: Henry, Dennis (Denny)

The Ocean Color Instrument team evaluates the instrument configuration in the Thermal Vacuum Chamber (TVAC) prior to closing the chamber door for testing. Credit: Mellos, Katherine

The Ocean Color Instrument team pushes the instrument into the Thermal Vacuum Chamber (TVAC) for environmental testing. Credit: Stover, Desiree

The flight Ocean Color Instrument is installed in the Thermal Vacuum Chamber (TVAC) for environmental testing. Credit: Mellos, Katherine

The Ocean Color Instrument is installed in the Thermal Vacuum (TVAC) chamber and prepared for thermal testing. Credit: Mellos, Katherine

Mechanical technicians crane lift the Ocean Color Instrument on to the Thermal Vacuum Chamber (TVAC) cart. Credit: Stover, Desiree

Quality engineer Luiz Mendez observes mechanical technician Tyere Garner remove bolts before lifting the Ocean Color Instrument from Tilt Mechanism to its ground support fixture. Credit: Henry, Dennis (Denny)

Mechanical technicians crane lift the Ocean Color Instrument from the Multi-purpose Ground Support Equipment (GSE) fixture. Credit: Henry, Dennis (Denny)

Mechanical engineer, Eduardo Rodriguez, and Mechanical Technician, Joe Eddy, prepare the vertical lift sling to crane lift the Ocean Color Instrument. Credit: Henry, Dennis (Denny)

Ocean Color Instrument Team poses with the flight instrument behind them in a cleanroom tent on August 4, 2022. Credit: Stover, Desiree

Eric Gorman & Robby Estep pose with the instrument and integrated earth shade and Tilt fixture in the acoustic chamber. Credit: Stover, Desiree

Ocean Color Instrument managers (Brian Clemons, Eric Gorman, Ulrik Gliese, Leland Chemerys, Joe Knuble, Robby Estep) pose with the instrument in the acoustic chamber. Credit: Stover, Desiree

The Earth Shade (ES) radiators on the Ocean Color Instrument are displayed as it is tested in a cleanroom at Goddard Space Flight Center. Credit: Stover, Desiree

Technician Nathan Allen connects the purge line to the Ocean Color Instrument in preparation for X-Axis (vertical) vibration testing. Credit: Stover, Desiree

Ocean Color Instrument mechanical team poses with the bagged instrument behind them after a successful environmental testing campaign. Credit: Stover, Desiree

Mechanical technicians transport the Ocean Color Instrument through the integration and testing complex to X-Axis (vertical) vibration chamber. Credit: Mellos, Katherine

The Ocean Color Instrument mechanical team stands on the balcony overlooking the bagged instrument after successfully installing it onto the X axis (vertical) vibration shaker table. Credit: Stover, Desiree

The Ocean Color Instrument mechanical team poses with the bagged instrument after successfully installing it onto the X-Axis (vertical) vibration shaker table. Credit: Mellos, Katherine

Thermal vacuum test of Ka-band Earth coverage antenna. Credit: Henry, Dennis (Denny)

The Ocean Color Instrument is crane lifted onto the Y-axis vibration table. Credit: Mellos, Katherine

The GSFC environmental testing team poses with the bagged Ocean Color Instrument in the acoustic chamber prior to testing. Credit: Stover, Desiree

Mechanical technicians crane lift the Ocean Color Instrument with Earth Shade onto the Flight Tilt Mechanism. Credit: Stover, Desiree

The Ocean Color Instrument integrated onto the Flight Tilt Mechanism with the Earth Shade. Credit: Stover, Desiree

The Ocean Color Instrument is prepared for environmental testing with installed thermal blankets, protective contamination covers, and flight Earth Shade (ES). Credit: Stover, Desiree

The Ocean Color Instrument (OCI) is prepared for environmental testing with installed thermal blankets and flight Earth Shade in a cleanroom at Goddard Space Flight Center. Credit: Stover, Desiree

The Ocean Color Instrument (OCI) team poses with OCI and its integrated Earth Shade in June 2022 at Goddard Space Flight Center. Credit: Stover, Desiree

Radiofrequency testing setup after spacecraft vibration test. Credit: Henry, Dennis (Denny)

Setting up for radiofrequency testing. Credit: Henry, Dennis (Denny)

The Ocean Color Instrument Electro-Magnetic Interference (EMI) & Electrical Ground Support Equipment (EGSE) Team pose in the control room at at Goddard Space Flight Center. Credit: Mellos, Katherine

The Ocean Color Instrument Electro-Magnetic Interference (EMI) Team pose in the EMI cleanroom at Goddard Space Flight Center. Credit: Mellos, Katherine

Ocean Color Instrument time lapse video showing the integration and build up of hardware from April 2021 to April 2022. Credit: Stover, Desiree

The Ocean Color Instrument is prepared for testing in the Electro-Magnetic Interference (EMI) chamber showing the Rotating Telescope side of the instrument. Credit: Mellos, Katherine

The Ocean Color Instrument is prepared for testing in the Electro-Magnetic Interference (EMI) chamber. Credit: Mellos, Katherine

PACE Control room. Credit: Henry, Dennis (Denny)

The Ocean Color Instrument Earth Shade (ES) is removed from a thermal chamber after successful testing. Credit: Mellos, Katherine

The GSFC Trax team lifts the Ocean Color Instrument on a forklift into a truck to transport to the integration and testing facility for envirnomental testing. Credit: Stover, Desiree

Lifting Structural Verification Unit out of chamber for the Sine Vibration Test. Credit: Henry, Dennis (Denny)

Installing Low Gain Antenna on PACE Spacecraft bus. Credit: Henry, Dennis (Denny)

Systems engineer, Joseph Knuble, adjusts the intensity of the studio lamp during the Ocean Color Instrument stray light testing. Credit: Stover, Desiree

Time-lapse video of lifting PACE Spacecraft SVU onto Aronson table, attaching Solar Array ETU, and lifting back to dolly at NASA Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Aligning the solar arrays and Structural Verification Unit to perform electrical tests. Credit: Lambert, Barbara

Lifting PACE Structural Verification Unit onto Aronson Table for engineering tests. Credit: Lambert, Barbara

Mechanical technician, Thomas Huber, integrates the Short Wave Infrared (SWIR) Pulse Calibration Assembly (SPCA) fold mirror assembly to the Ocean Color Instrument. Credit: Mellos, Katherine

Manufacturing engineer, Roman Nilov, supervises the integration of the Short Wave Infrared (SWIR) Pulse Calibration Assembly (SPCA) fold mirror assembly to the Ocean Color Instrument. Credit: Mellos, Katherine

Opened -Y Panel. Credit: Henry, Dennis (Denny)

Installing bus Star Tracker Sensor on the PACE -Z Panel. Credit: Henry, Dennis (Denny)

Installing the bus Star Tracker Sensor on the -Z Panel. Credit: Lambert, Barbara

Installing Star Tracker Sensor on the -Z Panel. Credit: Henry, Dennis (Denny)

Inspecting the PACE Star Tracker Sensor. Credit: Lambert, Barbara

Inspecting Ocean Color Instrument Star Tracker command and data handling unit. Credit: Henry, Dennis (Denny)

First powered deployment of the NASA PACE engineering test unit’s solar array drive assembly at Goddard Space Flight Center.

First powered deployment of engineering test unit’s solar array drive assembly. Credit: Henry, Dennis (Denny)

The Flight Ocean Color Instrument is installed onto the Ground Support Equipment Application for Tilt or Rotation (GAToR) Credit: Stover, Desiree

Inspection and electrical testing of PACE Flight Solar Array Panels. Credit: Henry, Dennis (Denny)

Alignment team working on the PACE spacecraft. Credit: Henry, Dennis (Denny)

Testing solar array drive assembly on PACE spacecraft bus. Credit: Henry, Dennis (Denny)

Installing the solar array drive assembly on the PACE spacecraft bus. Credit: Lambert, Barbara

Overall photos of Spacecraft after SADA install.

Overall photos of spacecraft after solar array drive assembly install. Credit: Lambert, Barbara

PACE spacecraft team checking alignment data. Credit: Henry, Dennis (Denny)

PACE engineering test unit for solar array drive assembly wing setup. Credit: Henry, Dennis (Denny)

PACE engineering test unit for solar array drive assembly walkouts on the gantry. Credit: Henry, Dennis (Denny)

Tightening bolts on the PACE engineering test unit solar array drive assemblies wing setup. Credit: Lambert, Barbara

Measuring PACE engineering test unit solar array drive assemblies wing setup. Credit: Lambert, Barbara

Carlos Duran-Aviles with the PACE reaction wheel assembly. Credit: Lambert, Barbara

Mechanical Technicians Daniel Dizon and Joseph Eddy transport the Ocean Color Instrument Earth Shade into the thermal vacuum chamber. Credit: Mellos, Katherine

Mechanical Technicians Daniel Dizon and Joseph Eddy install the Ocean Color Instrument Earth Shade into the thermal vacuum chamber. Credit: Mellos, Katherine

Mechanical technician Joseph Eddy and mechcanical engineer Peter Steigner install the Ocean Color Instrument Radiator Support Structure (RSS) struts to the Instrument Deck Structure (IDS). Credit: Stover, Desiree

Mechanical Technician, John Poulsen, installs flight hardware during the Ocean Color Instrument post Optical Module (OM) integration to the Flight Instrument Deck Structure (IDS). Credit: Mellos, Katherine

The Optical Module (OM) and the Flight Instrument Deck Structure (IDS) are integrated together, creating the Flight Ocean Color Instrument. Credit: Stover, Desiree

Mechanical Engineer Paul Dizon and Mechanical Technician Daniel Dizon with the Ocean Color Instrument. Credit: Stover, Desiree

Time-lapse video of closing +Y Panel and opening -Y Panel on PACE Spacecraft at NASA Goddard Spaceflight Center (23-Mar-22). Credit: Henry, Dennis (Denny)

Time-lapse video of working on the +Y Panel of PACE spacecraft at NASA Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Time-lapse video of installing the -Y panel on the NASA PACE spacecraft bus at Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Time-lapse video of installing a Qual Battery on the PACE Flight Spacecraft Bus at NASA Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Performing component functional testing on the PACE spacecraft. Credit: Lambert, Barbara

Members of PACE spacecraft integration and test team. Credit: Lambert, Barbara

Open panel (-Y) on PACE spacecraft bus. Blue electronics boxes are for the power system electronics (PSE) and command and data handling attitude control electronics box (CAB).

Open panel (-Y) on spacecraft bus. Blue electronics boxes are for power system and attitude control electronics. Credit: Lambert, Barbara

Installing qual battery on flight spacecraft bus. Credit: Henry, Dennis (Denny)

Mechanical technician Andrew Scharmann aligns the Ocean Color Instrument Focal Plane Assemblies (FPAs). Credit: Stover, Desiree

Panel (-Y) being installed on the spacecraft structure. Credit: Henry, Dennis (Denny)

PACE spacecraft bus structure. Credit: Henry, Dennis (Denny)

Time-lapse video of installing the -Y panel on the NASA PACE spacecraft bus at Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Assembling PACE spacecraft bus structure. Credit: Henry, Dennis (Denny)

Panel (+Y) installed on the PACE spacecraft bus. Credit: Henry, Dennis (Denny)

Installing panel (+Y) on the PACE spacecraft bus. Credit: Henry, Dennis (Denny)

Assembling PACE spacecraft bus structure. Propulsion tank is in the middle of the photo.

Assembling PACE spacecraft bus structure. Propulsion tank is in the middle. Credit: Henry, Dennis (Denny)

Checking the top of the PACE spacecraft bus structure.

View inside the PACE spacecraft bus structure. Credit: Henry, Dennis (Denny)

Installing the top of the PACE spacecraft bus structure. Credit: Henry, Dennis (Denny)

Checking the top of the PACE spacecraft bus structure. Credit: Henry, Dennis (Denny)

Time-lapse video of installing the -X panel on the NASA PACE spacecraft bus at Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

Installing of panel (-Z) onto the PACE propulsion module deck. Credit: Henry, Dennis (Denny)

Panel (-Z) installed on the PACE propulsion module deck. Credit: Henry, Dennis (Denny)

PACE spacecraft bus structure with -Z panel on propulsion module deck. Credit: Henry, Dennis (Denny)

Assembling PACE spacecraft bus (+Z and -Z panels) using keel lift. Credit: Henry, Dennis (Denny)

Time-lapse video of lifting the NASA PACE passive ring and propulsion module onto the observatory dolly at Goddard Space Flight Center.

Video of lifting the PACE passive ring and propulsion module onto the observatory dolly. Credit: Henry, Dennis (Denny)

Installing the passive ring and propulsion module onto the PACE observatory dolly. Credit: Henry, Dennis (Denny)

Lifting points proof test for spacecraft transport between facilities. Credit: Henry, Dennis (Denny)

Mechanical technician Andrew Scharmann stabilizes harnesses while Daniel Dizon rotates the Ocean Color Instrument Optical Module for additional integration activities as mechanical engineer Michael Mulloney observes. Credit: Stover, Desiree

Paula Cain and Aldine Joseph-Pierre apply thermal blanketing to the Ocean Color Instrument Loop Heat Pipes (LHP) prior to thermal vacuum testing. Credit: Mellos, Katherine

Electrical harnesses are installed and prepped for electronic box integrations on the Ocean Color Instrument’s Instrument Deck Structure (IDS). Credit: Mellos, Katherine

PACE assembly for structural testing. Credit: Henry, Dennis (Denny)

Mechanical technician Daniel Dizon stabilizes the Ocean Color Instrument Optical Module after a rotation for additional integration activities as mechanical engineer Michael Mulloney observes. Credit: Mellos, Katherine

Mechanical technicians reorient the Ocean Color Instrument Optical Module on the rotation fixture for additional hardware integration. Credit: Mellos, Katherine

The Ocean Color Instrument Optical Module (OM) at Goddard Space Flight Center. Credit: Stover, Desiree

Members of the Ocean Color Instrument Main Optics Sub Bench (MOSB) integration team pose with the hardware prior to its integration onto the Main Optics Bench (MOB). Credit: Stover, Desiree

Installing torque circular connectors during panel integration. Credit: Henry, Dennis (Denny)

Mechanical technician Joseph Eddy guides the Ocean Color Instrument Main Optics Bench (MOB) to the LISARD turnover fixture overseen by quality engineer George Brooks. Credit: Stover, Desiree

Blanket technicians discuss thermal templates on the Ocean Color Instrument Instrument Deck Structure (IDS) at Goddard Space Flight Center. Credit: Mellos, Katherine

Optical engineer, David Kubalak, inspects the Ocean Color Instrument Main Optics Sub Bench (MOSB) interior optics prior to covers are installed. Credit: Stover, Desiree

Ground system equipment setup for boresight alignment of HARP2 polarimeter. Credit: Henry, Dennis (Denny)

Group photo with HARP2 polarimeter. Credit: Henry, Dennis (Denny)

Reviewing data from the boresight alignment of HARP2 polarimeter. Credit: Henry, Dennis (Denny)

Ground system equipment setup for boresight alignment of HARP2 polarimeter. Credit: Henry, Dennis (Denny)

The Ocean Color Instrument Optical Alignment team poses for a group photo after successful alignment of the flight Main Optics Bench and Rotating Telescope assembly. Credit: Guinto, Michael

Performing electrical integration of engineering test unit’s Ka-band transmitter. Credit: Henry, Dennis (Denny)

Electrical integration of engineering’s test unit Ka-band transmitter. Credit: Henry, Dennis (Denny)

Video of second deployment of NASA PACE solar assembly mockup wing at Goddard Space Flight Center. Credit: Henry, Dennis (Denny)

PACE solar array deployment gantry. Credit: Guinto, Michael

Installing tilt and solar array drive electronics to a PACE spacecraft panel (-Y). Credit: Henry, Dennis (Denny)

Installing GPS receiver box to a PACE spacecraft panel (-Z). Credit: Henry, Dennis (Denny)

Installing stimulators on PACE course sun sensors. Credit: Henry, Dennis (Denny)

Performing electrical integration of flight power system electronics and engineering test unit’s command and data handling attitude control electronics box.

Performing electrical integration of flight power system electronics and attitude control electronics box. Credit: Henry, Dennis (Denny)

Lift fixture within thermal vacuum chamber. Credit: Seixal, John

Aerospace Engineer, Daniel Senai, inspects the completed Ocean Color Instrument Solar Calibration Assembly (SCA) Life Test Unit mechanism. Credit: Henry, Dennis (Denny)

Installed multilayer insulation thermal blankets on PACE propulsion module. Credit: Lambert, Barbara

Qualification of the spacecraft bus structure strength. Credit: Henry, Dennis (Denny)

Installing the flight propellant tank into the frustum. Credit: Dennis Henry

Assembling the structure and installing mass simulators and strength test fixtures

Assembling the structure, installing the mass simulators and tilt platform/solar array strength test fixtures, and assessing and demonstrating the panel G-Negation system functionality. Credit: Dennis Henry

Inspecting attitude control electronics box housekeeping telemetry for fluctuations registered during random vibration testing.

Inspecting attitude control electronics box telemetry for fluctuations registered during testing. Credit: Henry, Dennis (Denny)

Testing observatory lifting points and pull strength of tilt platform, solar array, SPEXone, HARP2, and bus star tracker interfaces. Credit: Henry, Dennis (Denny)

Lift of PACE spacecraft into the testing modal facility. Credit: Henry, Dennis (Denny)

PACE spacecraft structure with mass simulators and tilt platform and solar array strength test fixtures.

Spacecraft structure with mass simulators, tilt platform & solar array strength test fixtures. Credit: Henry, Dennis (Denny)

The optical alignment team performs gravity sag measurements on the Ocean Color Instrument Main Optics Sub Bench (MOSB). Credit: Stover, Desiree

Mass simulation assembly structure. Install of tilt platform/solar array strength test fixtures. Credit: Henry, Dennis (Denny)

Optical technician Timothy Hahn measures the Ocean Color Instrument Collimator Slit Bracket on the Coordinate Measurement Machine (CMM). Credit: Stover, Desiree

Technicians mechanically integrate the Shortwave Infrared (SWIR) Detector Assembly into the Ocean Color Instrument Engineering Test Unit. Credit: Stover, Desiree

Thermal integration of PACE propulsion tank.

Inertial reference unit electromagnetic interference testing procedure. Credit: Henry, Dennis (Denny)

Installing the ETU SDA onto the Turnover Dolly.

NASA Technician Andrew Scharmann verifies correct spring deflection to properly preload the depolarizer optic into the Flight Depolarizer Mount Assembly.

ETU SDA Post Delivery Acceptance Testing side view.

ETU SDA Post Delivery Acceptance Testing front view.

ETU SDA in its shipping container for post delivery to Goddard Space Flight Center.

The OCI ETU rolls into the TVAC chamber. Lines are for electrical connections, temperature sensors, accelerometers, and liquid nitrogen, whic is used for cooling down the radiators.

Preparing the OCI ETU and TVAC Cart to enter the TVAC chamber.

Lead Mechanical Engineer Mitch Zavala observes OCI ETU integration activities.

Quality Assurance (QA) Engineer Brad Weideman witnesses the OCI ETU hardware installation.

A mechanical engineer reviews integration documentation with the QA Engineer.

NASA engineers prepare for crane lifting of the OCI ETU.

De-integrating the OCI ETU in preparation for lifting to the Thermal Vacuum (TVAC) Cart.

Crane lifting the OCI ETU from the GAToR to the TVAC Cart.

The OCI ETU with the spinning telescope scanning the calibrated light source.

Beauty photo of the ETU OCI installed on the GSE Application for Tilt or Rotation (GAToR).

De-integration of the OCI ETU from the Transport Dolly.

Crane lift of the OCI ETU onto the Calibration and GSE.

Mechanical installation of the Data Acquisition Unit (DAU) electronics box onto the OCI ETU.

Mechanical installation of the DAU electronics box onto the OCI ETU.

Mechanical installation of the DAU electronics box to the mock-up ETU radiator.

MLA and Fiber Bundle linking the OCI OM to the SWIR Detection Assembly (SDA).

The OCI ETU with the OM installed and ready for Integration & Testing (I&T).

The OCI ETU with the OM installed and ready for I&T.

NASA technicians perform a flatness check between the OM and ETU Primary Structure.

Flatness check between the OM and ETU Primary Structure.

The fully integrated OM on the OCI ETU.

NASA technicians perform a flatness check between the OM and ETU Primary Structure.

The fully-integrated OM on the ETU.

The OCI ETU OM (with Red-Channel FPA installed) oriented for optical testing.

The OCI ETU MOB attached to the Lisard GSE prior to installation of MOSB.

The OM on Lisard GSE. Lift shackles are installed in preparation for an upcoming crane lift.

Unbolting the OCI ETU OM from the Lisard GSE in preparation for a crane lift move to the Instrument Structure. Protective contamination bagging is installed.

The OM is installed to the OCI ETU Primary Structure.

Crane lift of the ETU OM onto the OCI Primary Structure. (In order to protect the OM from potential particulate contamination and humidity, the OM is bagged and purged.)

Crane lift of the ETU OM onto the OCI Primary Structure.

The FPA installed on the ETU OM of the OCI.

Installation of the Focal Plane Assembly (FPA) on the ETU OM of the OCI.

The FPA installed on the ETU OM of the OCI.

Installation of the FPA on the ETU OM of the OCI.

MicroLens Array (MLA) and Fiber Optic Bundle attached to the OCI Optical Module (OM) during alignment and testing.

Alignment of the MLA and Fiber Optic Bundle to the OCI OM. The OM is located in the middle of the optical table.

Joe Thomas and Alejandro Rodriguez Perez perform alignment of the MLA and Fiber Optics Bundle to the OCI OM.

The MOSB installed onto the ETU MOB.

Integration of the populated ETU MOSB onto the ETU MOB.

The OCI ETU MOB attached to the Lisard GSE prior to installation of the MOSB.

The MOB attached to the Lisard Ground Support Equipment (GSE), prior to installation of the Main Optics Sub-Bench (MOSB).

Ocean Color Instrument (OCI) ETU FlatSat End-to-End Electrical System Test - LTU Electrical Integration.

Andrei Sushkov operating the OLAF-2 Goddard Laser for Absolute Measure of Radiance source bench (green light coming from the primary source class-4 laser).

Ultraviolet Visible Risk Mitigation Unit Dichroic Assembly.

Installation of the ETU HAM mechanism into the Main Optical Bench (MOB) structure.

Installation of the ETU Rotating Telescope mechanism into the main optical bench structure.

Alignment of the HAM mechanism in the MOB structure.

Assembly of the BOLT stack-up frame support structure.

A NASA technician installs an optic reference cube to the HAM mechanism in order to perform alignment measurements.

Installation of an optical cover to prevent any debris from contaminating the HAM mechanism optics.

A NASA technician assembles the Half-Angle Mirror (HAM) mechanism in preparation for balancing activities.

NASA technician, Wes Fincher, installs a temporary vibration sensor to prepare the ETU Rotating Telescope Assembly for dynamic spin evaluation.

Assembly of the BOLT unit stack-up prior to harness routing.

Assembly of the BOLT stack-up.

Setting up the Engineering Test Unit (ETU) for spindle axis characterization in order to measure the true spin axis of the mechanism.

NASA technicians assemble the BOLT unit into the vibration fixture.

Performing BOLT vibration testing. A contamination cover is installed to protect the hardware from debris.

A NASA technician installs the rotor mass simulator to the BOLT unit

A NASA technician installs the rotor mass simulator to the Bearing Only Life Test (BOLT) unit in preparation for vibration testing.

Click image to view slideshow.