WILLIAM B. PATTON SYSTEMS ENGINEER

***** ********* *****, ***********, ** 93314

acsfkq@r.postjobfree.com

661-***-****

Accomplished systems engineer with a proven ability to develop, test, and implement solutions to complex integrated advanced technical problems. Have led key initiatives that allowed success in aircraft test and development schedules. Recognized as an expert in advanced diagnostic systems and applying computer programming skills to those systems.

Background in many aspects of advanced aircraft lifecycle, including systems development, systems test, aircraft maintenance, and legacy aircraft depot support. Including over 10 years' experience providing thorough and skillful system reliability analysis support. More than 15 years of aircraft support programming experience, with strong analytical skills and a broad range of computer expertise. Experience writing test procedures, supporting software tools, system integration of hardware and software, system level analysis and troubleshooting, data analysis, developmental test, and qualification test. An organized, detail-oriented, and conscientious self-starter, able to strategize and prioritize effectively to accomplish multiple tasks and stay calm under pressure. A skilled integrator; able to synthesize and deliver complex information to diverse disciplines.

Experience & Contributions

LOCKHEED MARTIN AERO COMPANY

Joint Strike Fighter(JSF) design, development, testing, and production

Flight Test Engineer

461st Flight Test Squadron, F-35 Flight Line Engineering Department

225 N. Flightline Rd, Edwards AFB CA 93524

9/2010 to 11/2014

Improvement in F-35 Operational Test flights and readiness rates and reliability was accomplished by performing and directing engineering investigations for the F-35 Operational Test Support Team (31TES, Edwards AFB, CA) malfunctions and faults. Including:

Resolved F-35 subsystem faults that were not documented in the Autonomic Logistics Information System (ALIS), fault logs, or downloaded data.

Corrected faults for both air vehicle and missions systems.

Underwent engineering investigations as to the causes of failures and lack of functionality.

Provided technical support and feedback regarding causes

Using historical documentation and records, directed repair actions

Used fault codes in addition to communication with Lockheed Martin and the propulsion contractor (Pratt) to isolate and determine malfunction causes.

Diagnosing, analyzing, and reporting fault data in an accurate and concise manner.

Initiated support for the Marine Operational and Evaluation Squadron 22 (VMX-22) for coordination, documentation, and resolution of aircraft malfunctions and faults. Included their BF19, BF20 STOVL jets.

F-35 Integrated Test Force (ITF) Edwards AFB CA (EAFB) Prognostics and Health Management (PHM) Lead. PHM is an advanced fighter aircraft integrated vehicle health monitoring system. Provided direction in support of the maturation of PHM.

Included developing, testing, and fielding of PHM.

Processed detailed PHM data to determine root causes to aircraft faults.

In support of flight testing operations for the F-35, a Department of Defense (DoD) application.

Specialized extensive F-35 air vehicle systems engineering related development activities including:

Developing the proper failure detection, isolation reporting for the flight control system (FLCS).

Analyzed fault codes associated with the AF1 external/internal stores pit tests for any expected/unexpected faults.

weapons integration system fault detection development.

fire protection system sensor fault detection development

Navigation: INS, GPS, FLCS system integration fault detection development

Worked IPP startup fault detection issues and resolution.

Evaluated and made recommendations on the main landing gear (MLG) pressure sensor strut length design improvement.

Researched failure detection methodology for the INS drift phenomenon. INS needed to be zero-d to clear the fault and green up the jet.

Identified and troubleshot faults related to the electrical power system. For example: F-35 at 28V batt on the AMD comes up. Then the pilot selects IPP on. This powers up 270V and the PMD comes up. The 28V battery will fail and no cause will be detected.

Contributed to the F-35 AF2 accomplishment of 1000 flt hrs 6/18/14 by ambitious resolution of faults.

Interpreted the fault data output as processed by ALIS. Reported the results to Subject Matter Experts (SME) and Integrated Product Team (IPT) engineers.

Educated and teamed with the Flight Test Control Engineers (FTCE) regarding the use of the PHM system within the ALIS aircraft maintenance processes.

Wrote, taught, and implemented the processing of PHM data from the jet, to the PMD, through OMS and the Ground Data Receptacle (GDR) into Squadron Health Management (SHM) and the Computerized Maintenance Management System (CMMS).

Allowed more precise reporting of the prognostics reliability performance to the Joint Program Office (JPO) by accurately researching, analyzing and scoring aircraft maintenance data for the Reliability and Maintainability Review Board (RMRB).

Provided guidance to discipline engineers which enabled the F-35 missions systems fusion design and architecture to perform to its requirements by developing an understanding of this design to best interpret the failure signature, from the functional level to the board level and to the software fault level. This includes MADL, Link 16, PPL.

Improved the mission systems PHM maturity in a matter of months which enabled successful completion of numerous mission systems flight test points including sensor testing points. Aggressively resolved mission systems PHM issues.

Enabled discipline engineers to better understand their systems in a dynamic integrated environment which led to better performance of those respective systems by researching, troubleshooting, analyzing, and characterizing faults.

These systems include Communications, Navigation, Interrogation (CNI), Electronic Warfare (EW), Integrated Core Processor (ICP), Counter Measures (CM), Radar.

Interpreted and matured the PHM resulting fault signature by developing a working knowledge and understanding of each of the mission systems at the flight test level.

Independently initiated and performed reviews of low level PHM data by finding the tools, working with the owners of the tools, and mastering understanding of the tools.

Resolved mission systems faults (including GPIO, GP, SPIO, SP modules) on the aircraft by leading the PHM portion and participating in the triage telecons and by providing PHM diagnostics results.

Used technical background and experience to develop methods to collect, analyze, and report diagnostics technical data related to aircraft systems, missions systems, and various support systems.

Processed and analyzed the missions systems binary and hex low level fault data using SIMS and EPIC. Interpreted and reported the results. Coordinated the end-to-end process of PHM fault detection from the aircraft to the end user.

Assisted SMEs by analyzing Integrated Analysis & Data System (IADS) signal results after flight.

The PHM page is a page on the cockpit display that allows the pilot to assess the health of his jet. This display is insufficient to provide accurate, timely, and clear representations to the pilot.

Wrote flight test plans and flight test cards for the pilot to perform measurements and tests of the PHM page during flight.

Developed flight test procedures for the pilot to execute tests of the PHM page. Provided input to the design team to modify and improve this page.

Wrote deficiency reports to document and track improvements of this page.

Participated in the PHM debrief process of the jet. Presented immediate health diagnosis flight test results to the pilot and discipline engineers. Led this portion of the debrief. Documented and reported anomalies and issues.

Provided analytical results of the weapons integration fault data for the internal weapon bay JDAM (Joint Direct Attack Munition) drop tests for the F-35 aircraft (AF1).

Documented and verified the related faults, coordinating input with the cognizant on-site Weapons Integration SME (subject matter expert).

Monitored improvement of the associated faults over time, looking for trends and maturing the fault detection of the F-35 weapons drop capability.

LOCKHEED MARTIN AERO COMPANY

F-22 Air Superiority Fighter Test and Sustaining Engineering

Staff Systems Engineer

411 Flight Test Squadron, F-22 Combined Test Force (CTF)

365 N. Flightline Rd, Edwards AFB CA 93524

6/2005-9/2010

Specialized in-service sustaining engineering support of the F-22 flight test aircraft. Specific accomplishments included:

Wire harness, cabling, and connectors sustainment engineer. Trended, reported, analyzed, and made improvement recommendations for wiring and its installation in the F-22 fielded aircraft. Used JEDI for wire tracing. Used MS Excel cross-tab reports for failure analysis.

Investigated historical R&M data for possible high failure rate causes of the aircraft 4006 nose landing gear collapse factors, including the landing gear control panel or weight on wheels switchology.

Researched Mar 2009 F-22 4008 crash for possible R&M contributing causes due to items with high failure rates. Provided results to management for the safety and accident investigation boards.

F-22 would cause an IFE due to Air Cooling ICAW. This was due to the high altitude, not a functional failure. Faulty design of an environmental control system (ECS) component caused the IFE. Researched failure trends and results to design engineering.

Tracked F-22 small diameter bomb (SDB) modification for R&M impacts.

At System Program Office (SPO) and CTF modification team request, identified appropriate CTF failure modes in need of Reliability and Maintainability Maturation Program (RAMMP) project resolution. Recommended RAMMP projects for CTF aircraft inclusion. Advised IPT representatives of said projects.

Answered quality assurance (QA) and product engineering questions regarding part history and historical configurations. Funds were saved as a result of locating, identifying, and utilizing proper configurations with these efforts.

Reviewed and tracked Spiral 2 and Lot 5 modifications on the EAFB aircraft for R&M deficiencies. Researched the R&M performance of the CTF test aircraft. Incorporated results into CTF SEDS to be used by the customer, the SPO. In addition, this data is used to develop CTF R&M metrics for reporting purposes.

Submitted weekly CTF Common Problem Reporting System (CPRS) Spiral 2, Lot 5, and Lot 6 status updates to avionics management.

Submitted weekly R&M CTF status reports regarding SDB and AIM-9X modification efforts. These reports are sent to product engineering and management to assist in their decision making.

Managed and tracked the reliability improvement project: wing-tip lighting. The original design was not as efficient and low reliability. The upgrade was a light emitting diode (LED) design. Tracked modification, performance, and reliability. Reported results to IPTs and management.

LOCKHEED MARTIN AERO COMPANY

F-22 Air Superiority Fighter Flight Test Reliability, Maintainability, Supportability

Contractor R&M Lead

411 Flight Test Squadron, F-22 Combined Test Force (CTF)

365 N. Flightline Rd, Edwards AFB CA 93524

2/1998-6/2005

Represented Lockheed Martin Aero Company as the prime technical contact for R&M at the CTF. Managed the F-22 CTF R&M program. Coordinated all issues and proposed resolution with the CTF R&M government counterparts. The CTF R&M organization has members from each contractor, USAF civil service, and suppliers. This represents diversity in viewpoints and approaches to reliability. Improved the organizational synergy by making proper judgments, using coordination ability, and properly being able to influence and motivate others. Used motivational techniques and change methods to ensure effective relationships. Defined R&M job responsibilities. Trained and monitored new employees.

CIP, CNI, EW, IRS, C&D CTF R&M OPR. Analyzed, tracked, and categorized failure events and modifications on these subsystems. Required an understanding of the functions of each discipline as well as their interfaces. Researched, studied, and documented failure modes and their effects. Correlated events to those with similar failure modes. Presented results at the JRMET.

Supported air vehicle engineering by tracking these failures using the system squawk list (SSL). Managed and reported system failures events to the team and management.

JRMET Secretary. Administrated JRMET meetings. Assisted IPTs in disposition of failures & provided resolution to JRMET for adjudication. Led and provided direction for fix effectiveness and fix demonstration efforts. Supported all JRMET meetings with review and evaluation of reliability failures. Took minutes, documented disputes, assisted resolution of disputes, and coordinated answers to action items. Represented Lockheed Martin (the company) CTF R&M at JRMET VTCs and conference calls.

Supported all Joint Reliability Maintainability Evaluation Team (JRMET) meetings with review and evaluation of reliability failures. Documented disputes, assisted resolution of disputes, and coordinated answers to action items.

FRACAS Team Lead. Ensured FRACAS guidelines are sufficient to perform FRACAS requirements. Installed and tested CTF failure analysis databases. Wrote FRACAS Upgrade specification, mockup, and schedule (Microsoft Project). Ensured that FRACAS functions as a closed loop failure analysis and corrective action system as required by the Air Vehicle specification.

Provided FRACAS weekly summary status to CTF Director.

Applied reliability analyses in the form of statistical and regression analyses and hypothesis testing to assist the Integrated Product Teams (IPTs) in the determination of which systems are performing below requirements.

Interfaced with QA, supply, ground operations, flight operations, etc., as needed to assist their Failure Reporting Analysis and Corrective Action System (FRACAS) activities and efforts.

Served as focal point for describing failure details for CTF failures.

Participated in the JSF FRACAS supplier downselect process between FavoWeb and Relex in Ft Worth.

CTF CPRS Board Member. Managed CPRS (Common Problem Reporting System) for CTF. Directed the writing of procedures for using CPRS which is hosted on the classified S/SEE under PCMS. Supported AVIT (Air Vehicle Integration Team) by representing the CTF. Loaded, statused, verified, and closed CPRs originated at the CTF. Verified dispositions of CPRS events. Loaded CPRs for CTF failure events as directed by engineering. Provided information as needed to the IPTs to resolve these issues.

Managed contractor support for the USAF Watch Item/Deficiency Report (WIT/DR) Board which consisted of program office engineers and logisticians.

Ensured that the deficiencies identified by WITs were being properly identified, tracked, documented, and coordinated with the contractor home teams. Statused events that have been worked in CPRS. Updated dispositions with maintainers and engineers. Loaded CPRs for WITs as directed by the WIT Board.

Provided detailed input, researched technical questions, clarified problem descriptions, and forwarded background information.

Assisted IPTs in determining which installed components and subsystems were performing below requirements. Ensured all pertinent failure data was collected and documented for each failure and maintenance action of all IPTs. Ensured complete failure information was being entered into government IMIS database.

Ensured maintainability engineers properly troubleshot failures, access areas on the aircraft to repair, perform appropriate repairs, test and verify fixes, and document resolutions.

Utilized information systems such as MS Outlook/Exchange, CATIA, Windows NT, Classified S/SEE, UNIX, RTM, Interleaf, Oracle, CTF Intranet, MS Office, MS Access, Visual Basic, SEDS database, FRACAS, Sybase, and PowerBuilder.

Coordinated R&M rules, scoring method with propulsion system engineers (PW).

Provided reliability guidance and decision-making as the F-22 EMD flight test contractor reliability lead for engineering and manufacturing development (EMD) exit criteria.

Compared operational test reliability entrance and exit criteria for readiness, suitability and effectiveness.

Monitored, managed, tracked, and reported reliability growth for the fix demonstration and fix effectiveness evaluation statistical methodology.

Scored, recorded and documented contractor reliability performance results for F-22 IOTE, FOTE1, FOTE2 per OT test scoring procedures. Reported to contractor management.

Reviewed, documented, and tracked contractor manufacturing quality assurance reports (QAR) for EMD R&M metrics impacts. The QARs would reflect failure trends that continued on flight test jets. These trends effected the resulting metrics.

Supported several flight test missions with mission control room (MCR) support.

LOCKHEED MARTIN AERO COMPANY

F-22 Air Superiority Fighter Reliability, Design, and Development

Product Support Engineer

Bldg L-22, Marietta, GA 30063

10/1995-2/1998

Performed reliability and integrity support to accommodations, canopy, escape, armament, and life management IPTs.

Evaluated subcontractor proposals; engineering liaison between subcontractors and Lockheed (LASC); analyzed subcontractor reliability and integrity data, models, qualification test procedures and reports, and systems verification and validation documents; coordination and closure of reliability and integrity Integrated Master Plan (IMP) tasks (FMECA, integrity reports, FRACAS, trade studies) to support successful First Flight Readiness Review (FFRR), performed statistical analysis and generate modes (as required) for reliability and integrity Analysis and Integration (A&I). Managed and coordinated input and changes to the Life Management Plan (LMP).

Performed an audit of the team FMECAs as the FMECA Team Lead (MIL-STD-1629A). Ensured the FMECAs contained vertical and horizontal links. Ensured they properly documented failure mode indicator assignment (FMI) and risk hazard analysis (RHA) per MIL-STD-882.

Wrote the air vehicle/engine integration FMECA. Wrote a White Paper stating the analysis and results of this FMECA.

Reviewed Supplier Data Requirements List (SDRL) documentation for supplier compliance to reliability requirements. Coordination of resolution of conflicting reliability requirements. Trained junior reliability engineers regarding FMECAs and reliability predictions. Wrote cockpit system FMECAs for CDR. Interfaced with other company disciplines in the writing of the FMECAs. The disciplines included integrity, safety, design, environment, etc. Coordinated with Boeing and LM-Aero-FW regarding the FMECA interfaces. Presented schedules for completion of reliability tasks. Analyzed cockpit integrity reports for life management impacts.

Reviewed CATIA drawings for integrity/reliability impacts. Recommended design changes as needed based on reliability assessment. Reviewed supplier PDR submittals. plans, reports, and SDRLs for integrity (forces, thermal, damage tolerance, durability control points (DCP), key characteristics (KC), variability reduction program (VRP) etc.) and reliability (FMECA, predictions) issues. Addressed these issues with the supplier and LASC. Coordinated supplier SDRLs with a variety of LASC disciplines.

Reviewed the RMT&S Plan, Logistics Test Plan, etc. for reliability systems verification and validation (V&V) guidance. Skilled in the workings of the classified Software/Systems Engineering Environment (S/SEE). Reviewed the Reliability Test Information Sheets (TIS) in the Requirements Traceability Matrix (RTM). Documented system integration anomalies in the team failure resolution database, the Common Problem Reporting System (CPRS).

Performed reliability and integrity support for the design and development of the F-22 aircraft. Accomplishments included:

Evaluated F-22 canopy design this design for reliability impacts. Worked with the supplier, Sierracin and materials and processes engineering for supportability improvements and requirements including prisms for viewing cracking.

Assessed and made recommendations to improve the canopy system reliability by evaluating the canopy actuator brake mechanism for reliability impacts.

Extensive effort reviewing the reliability performance of the F-22 cockpit and armament systems by analyzing the impact of environmental stress screening (ESS).

Improved the proposed spares rate by evaluating the reliability growth curves for the cockpit systems.

Improved ejection system reliability by addressing issues from qualification testing, including sled testing, and salt fog testing.

Improved the accuracy and effectiveness of the external lighting system reliability predictions by evaluating the supplier statements of work regarding Weibull distributions.

The F-22 external pylon experiences a harsh environment. Assessed the reliability impacts of the integrity of this environment and reported that to management.

Improved F-22 reliability predictions by assessing the accuracy and results of acceptance test procedures (ATP). For example, infant mortality, wearout. Developed a proposed checklist for ATPs.

Improved the F-22 cockpit design by analyzing its vulnerability performance. Reported results to management for inclusion in future modifications and design changes.

Performed analysis of the accommodations system (cockpit instruments and control switches) for reliability impacts. This included an assessment of the reliability predictions allocation from the air vehicle reliability requirements. Ensured that there was traceability for these predictions. Verified the predictions were met by analysis or test. Documented and reported results.

Ensured F-22 cockpit reliability performance was on track by reviewing data documented in the Logistics Support Analysis Record (LSAR).

Participated in the external fuel tank downselect process.

US GOVERNMENT CIVIL SERVICE

Advanced Tactical Fighter Logistics and Sustainment

Aerospace Engineer

F/A-22 System Program Office, Logistics Support Division

F/A-22 Support Systems Branch

SM-ALC/YFLB, McClellan AFB, CA 95652

6/1991-10/1995

Identified logistics supportability impacts to system/equipment designs and proposed engineering changes/alternate solutions to avoid adverse impact. Specific tasks included:

Performed reliability, maintainability, and supportability (RM&S) analysis of F-22 data in the Logistics Support Analysis Report (LSAR) on F/A-22 weapons systems including main weapons bay doors, side weapons bay doors, pylons, LAU-128 launcher, 20-mm gun, ammo system, software controls interacting with the missile launch profile, pilot controls, etc

Evaluated missile velocity and acceleration loads upon ejection and under weight constraints. Evaluated aerodynamics and aerodynamic missile loading. Analyzed vibration and structural loading. Contributed to overhaul procedures development. Analyzed fluid flow performance parameters.

Evaluated the mechanical systems integrity program data and reports for RM&S concerns. Inspected the F-22 engineering drawings for RM&S suitability and accuracy.

Selected support/test equipment candidates for the F-22 hydraulics, fuels, and armament systems, including the weapon bay door drive system and the launchers. Analyzed the reliability and maintainability figures given in the database for the systems. Established reliability growth based on analysis.

Reported to the SM-ALC/YFL branch chief of R&M issues and development status for these systems.

Provided input to the identification of depot source of repair and engineering/technical support requirements for assigned systems in preparation for Operational and Support (O&S) phase.

Evaluated program continuously for opportunities to increase system reliability and maintainability and recommended measures for improvement. Performed an RM&S analysis of F-22 data in LSAR on assigned systems or subsystems.

Assured timely identification of program needs and recommended changes in work procedures and performance goals to enhance the quality of organization work life and products.

Interfaced at the technical level with other F-22 IPT members on issues of F-22 support.

Developed the F-22 Life Management Plan. Provided a presentation to the System Program Office (SPO) at Wright-Patterson AFB, OH.

Reviewed the F-22 Vehicle Systems Statement of Work (SOW), Integrated Master Schedule (IMS) and Integrated Master Plan (IMP). Determined and provided input to both the contractor and branch chief any scheduling concerns. Used the IMP/IMS to assess contractor and SPO-West scheduling and planning efforts.

US GOVERNMENT CIVIL SERVICE

USAF Sustaining Engineering Support

Aerospace Engineer

Directorate of Materiel Management, A-10/Misc Acft/ILP Sys Mgt Division

Systems/Avionics Engrg Section

SM-ALC/MMSRD, McClellan AFB CA 95652

8/1982-6/1991

Designed and integrated modifications used on high-performance aircraft, e.g., pilot environmental filter, emergency canopy jettison, and ejection-seat not armed light modifications.

Performed structural loads analysis on: seat jettison, gatling gun torque, accumulator strap vibration, and windshield loads. Analyzed engineering drawing packages for accuracy.

Performed tech order verifications, inspections, and procedures. Developed kit proof procedures and prototype efforts on modifications.

Selected between aluminum, steel, titanium, chrome, and other materials for use on aircraft modifications. Evaluated bolt strengths, sized, and types. Evaluated material response to high impulse loads, vibration in electronic components, galvanic corrosion, and sealant and adhesive applications in adverse environments. Analyzed complex system for use on aircraft including stall devices, windshield patching schemes, etc.

Projects included aircraft and support/test equipment improvements and modifications. Developed solutions to aircraft problems i.e., repairs to structural cracks, switch failures, weight and balance problems. Analyze performance deficiencies in the A-10 aircraft including aircraft drag producers. Drafted, reviewed, and verified technical order procedures. Developed acceptance criteria for canopy system modifications, including load, vibration, and performance. Wrote contracts for private industry to evaluate aircraft flight loads. Reviewed contractor-generated analyses.

Performed aircraft sustainment modifications (A-10, T-39, T-33) in support of the USAF depot.

A-10 System Safety Group Administrator, created agenda, wrote action items, wrote minutes, statused events.

Evaluated vendor proposed Engineering Change Proposals for requirements, feasibility, completeness, accuracy, cost and operational and logistic impact.

Extensive in-service sustaining engineering support of the A-10, T-33, T-39 air vehicles. This included responsibility for the engineering accomplishment of modifications and arrangement of support services such as engineering, drafting, material acquisition, parts manufacture, prototype, system checkout, ground and flight testing. Planned, organized, coordinated and controlled entire engineering projects. Drafted and disseminated Time Compliance Tech Orders (TCTO) in support of fleet (or force) modifications or notices. Ex: A-10 center windshield crack criteria.

Provided technical support, analyzed damage from fielded aircraft subsystems for fleet maintainers and operators. Examples:

Developed, designed, tested, and fielded a pilot chem-bio air-breathing system for the A-10 aircraft

oIn support of Desert Storm, 1990

oEjection seat tower tested at the Naval Air Development Center, Warminster, PA

odesigned in 3-dimension space on computer workstation

omaintained a schedule and budget for this design effort

Coordinated A-10 repairs by communications with A-10 contractor, Fairchild Republic, Farmingdale, NY

Characterized the nature, size, number of A-10 center windshield cracks. and developed criteria for crack length, depth, amount. This was successfully used by the field.

Developed inspection process and criteria for A-10 canopy transparency bolt hole cracking using refractory technology. Implemented this process in the field.

Developed, tested, and fielded an improved A-10 canopy rig procedure. Existing rig procedure was inadequate and inaccurate.

Redesigned A-10 flight control actuators to lower the installation tolerances. Thereby removing slip and permitting better control of flight, particularly in manual reversion mode.

Directed engineering investigation including laser technology of A-10 canopy unlock problems which caused a safety incident at Nellis AFB NV.

Developed and fielded T-33 ejection seat removal procedure. Utilized crew chief experience and knowledge. Documented the procedure in formal tech data.

A-10, T-33 Systems Safety Group (SSG) Secretary - coordinated, managed, provided feedback to A-10 pilots and "fleet operators" for these fielded jets

Drafted, coordinated, wrote and distributed to the A-10 fleet operators messages regarding engineering issues, e.g., ejection seat modifications, time change items, etc.

Relevant Coursework:

Graduate, Air Command and Staff College, Jun 1988

USAF Mishap Investigation 2-week course at Norton AFB, CA. WCIP 05A

A-10 canopy rigging school, Davis-Monthan AFB, AZ Nov 1987

ACES II ejection seat maintenance school, Myrtle Beach AFB, SC

Aircraft General Weight & Balance course, McClellan AFB, CA May 1990

AFIT Test and Evaluation

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