Experience

AMSL Aero

• Australia
• Airlines and Aviation
• 1 - 100 Employee

• Senior Aero structures Engineer

  • Apr 2019 - Present

  Structure design and analysis of an electrically powered aircraft. Structure design and analysis of an electrically powered aircraft.



Amce

• Aviation and Aerospace Component Manufacturing
• 1 - 100 Employee

• Senior Structures Engineer

  • Oct 2016 - Mar 2019

  Structural deviations and mods on; C130J, C130H, C27J and E-7A Wedgetail. Structural deviations and mods on; C130J, C130H, C27J and E-7A Wedgetail.



Yamaha Motor Australia Pty Ltd

• Australia
• Motor Vehicle Manufacturing
• 1 - 100 Employee

• Lead Stress Engineer

  • Feb 2015 - Aug 2016

  Program: Rotor Wing System R&D Task: Loads / Structural Analysis / FEA / Design Optimization / Testing. Optimization of metallic and composite structures using Altair HyperWork software on a fast moving R&D project. Aspects considered include structural strength, natural frequency response and buckling. In addition a large number of fasten and welded structural joints were sized. Final substantiation was successfully done by test. Program: Rotor Wing System R&D Task: Loads / Structural Analysis / FEA / Design Optimization / Testing. Optimization of metallic and composite structures using Altair HyperWork software on a fast moving R&D project. Aspects considered include structural strength, natural frequency response and buckling. In addition a large number of fasten and welded structural joints were sized. Final substantiation was successfully done by test.



Quest Global

• Singapore
• IT Services and IT Consulting
• 700 & Above Employee

• Technical Specialist

  • Dec 2011 - Dec 2014

  August 2013 – December 2014 Technical Specialist Program: Airbus Single Aisle - A319/A320/A321 Task: Wing ribs and aft pylon fitting F&DT certification Checkstress. • Approval level checking of Wing Ribs and Dry Bay F&DT Checkstress and Rib Stress Survey dossiers for the introduction of the New Engine Option (NEO) wing with the new larger winglet (Sharklet). • Approval level checking of Wing Ribs and Aft Pylon Fitting F&DT Checkstress and Rib Stress Survey dossiers, for the introduction of the wing with the new larger winglet (Sharklet). • This included a two months relocation to the Airbus Engineering office in Wichita, Kansas, USA (mid Oct. 2014 to mid Dec 2014). During this period internal Airbus technical approval (level 2) was granted and applied to these reports. Under the Airbus supplies quality system this approval could not be granted externally through QuEST Global. August 2012 – July 2013 8 months at the Airbus Americas Engineering Wichita office and the remainder in Australia. While at AAE held both Approval and Authorisation delegation. Technical Specialist Program: Airbus A380 Task: A380 Wing Rib Serial Solution F&DT Analysis and Checkstress. • Approval of F&DT Checkstress dossiers for the rib body analysis. • Supporting the analysis of the redesigned rib feet. • Supporting initial drawing release of new metallic ribs • Approval, authorisation and part author of Modification Structural Justification Technical Reports (e.g. L57RP1261522). Dec 2011 – July 2012 Technical Specialist Program: Airbus A400M Task: Team leader with Airbus Approval • Technical lead and approval on the Fatigue and Damage Tolerance (F&DT) Checkstress analysis of the A400M Fix Trailing Edge Aileron, Spoiler and Flap Groups composite shroud panels and metallic attaching structure. Show less



GKN Aerospace

• United Kingdom
• Aviation and Aerospace Component Manufacturing
• 700 & Above Employee

• Technical Specialist

  • May 2001 - Dec 2011

  Program: Airbus A400M, A310 and F35 CTOL Task: Team leader with Airbus Approval • Technical lead and approval, Fatigue and Damage Tolerance (F&DT) Checkstress analysis of the A400M Fix Trailing Edge Aileron, Spoiler and Flap Groups composite shroud panels and metallic attaching structure. • Technical lead and approval, A310 SRM Static Strength justification for the Fix Trailing Edge structure, to meet the obligations of the Ageing Aircraft Act. • Approval of the stress analysis on the A400M Fix Trailing Edge wing structure for both metallic and composite on the Entry into Service (MSN006) configurations. • Team lead and technical approval, F&DT analysis of the A400M Fixed Trailing Edge Structure for the MSN001 configuration. • Analyst on the JSF (F35) CTOL Upper Skins and Panels. . • FEM checks and alterations on the JSF (F35) CTOL forward fuselage. Mar 03 – Jan 05 Program: Outer Suburban Electric Rail Car Task: Vehicle Structure • Acting as Lead Senior Structural Engineer to a team of Structural Engineers on the Car Body of a Double Decker Electric Motor Unit Passenger Rail Car design build project. • Representing the client with the customer and responsible for the structural integrity of the car body, while producing an optimised design. • Interfacing with the various subsystem owners to provide the necessary support and access required. • Providing manufacturing support during the prototype and production stages. • Utilising PATRAN and NASTRAN to solve more difficult and complex structural issues. May 01 – Mar 03 Program: Airbus Continuous Product Development (CPD) Task: Sydney office manager • Providing the Sydney team with leadership, technical and content support on AIRBUS UK work packages. • Local team and technical lead on various AIRBUS UK work packages, includes the A318 F&DT wing checkstress and other Airbus CPD projects. • Lead level 2 checker on A340-500/600 SIA wing covers F&DT checkstress. Show less



Hawker de Havilland

• Bankstown, Australia

• Senior Stress Engineer

  • May 1997 - May 2001

  Program: Airbus A340-500/600, Bombardier BD100 and DASA Task: Composite and Metallic Structures • Overseeing a team of up to 4 Engineers on the BD100 Tailcone Flight Test Article. Finite element modelling and static analysis to verify the structural design. Creation of the structural justification and FEM reports. • Structural Engineering Team Lead on the A340-500/600 Winglet and Tip design, from C-scheme concept to production. Responsible for structural justification and strength approval, including static, fatigue and damage tolerance. • Working with the CRC-AS (Composite Research Consortium) in the analysis of a composite form rib being developed with DASA. Involved Finite Element Analysis (PATRAN/NASTRAN) and compiling a stress report to support testing in Germany. Show less



A Goninan & Co. Ltd

• Newcastle, Australia

• Structural Engineer

  • Oct 1995 - Apr 1997

  Program: Trains, Locomotives and wagons Task: Body structures • KCR Light Rail vehicle; design and validation of car body structure using Finite Element Analysis (PATRAN/NASTRAN). Supporting the strain gauge testing program, provide manufacturing liaison and create technical reports. • Complex 3D solid model of the Hunter Coal Wagon Bogie Axle Box, with design optimisation for minimum weight. • Analytical support to other projects. Program: Trains, Locomotives and wagons Task: Body structures • KCR Light Rail vehicle; design and validation of car body structure using Finite Element Analysis (PATRAN/NASTRAN). Supporting the strain gauge testing program, provide manufacturing liaison and create technical reports. • Complex 3D solid model of the Hunter Coal Wagon Bogie Axle Box, with design optimisation for minimum weight. • Analytical support to other projects.



Hawker de Havilland

• Bankstown, Australia

• Stress Engineer

  • May 1995 - Sep 1995

  Program: Lockheed Hercules C130J Task: Composite flap project • Detail analysis using hand calculations, Lockheed software and discrete finite element models. Program: Lockheed Hercules C130J Task: Composite flap project • Detail analysis using hand calculations, Lockheed software and discrete finite element models.



Eagle Aircraft

• Henderson, Western Australia

• Aeronautical Engineer

  • May 1994 - Apr 1995

  Program: Eagle X-TS (VLA aircraft) Task: Liaison/Production Support • Production support role on the Eagle X-TS aircraft. Responsibilities include resolving manufacturing non-conformances, evaluating changes and amendments to the engineering configuration. Static and fatigue analysis of composite/metallic skins/panels in fuel tank region and metallic secondary structure brackets/intercostals. Worked these parts from layouts through to detail drawing release. In addition to this, was also involved with the sizing and placement of testing instrumentation (strain gauges) Show less



Ricardo Aerospace

• Chipping Sodbury, UK

• Stress Engineer

  • Mar 1992 - Apr 1994

  Program: Airbus Task: Wing Fatigue and Damage Tolerance • Fatigue, fracture mechanics and damage tolerance analysis on the lower wing surfaces on the Airbus A330-300, A340-300 and the A321-100 flap tracks. • Crack propagation prediction work carried out on test panels, with features such as manholes, spanwise and chordwise skin joints. • Analysis to substantiate standard allowable repair limits. • Work required customer liaison and the ability to interpret and understand the client’s methodology and software. These tasks were under the responsibility of Airbus UK engineers Mr. S. Y. Bell and Mr. J. Eisensoe. Worked individually to design modifications to subsystem equipment to improve efficiency of a brake press. Show less



Westland Aerospace

• Isle of Wright, UK

• Stress Engineer

  • Nov 1990 - Dec 1991

  Main Program: McDonnell Douglas MD-11 Task: Centre line engine duct assembly • Strength analysis, design evaluation and report preparation, of the aluminium alloy substructure of the MD-11 centre line engine duct assembly. • Finite element analysis of the BAe Jetstream 41, KEVLAR engine oil cooler exhaust duct. Main Program: McDonnell Douglas MD-11 Task: Centre line engine duct assembly • Strength analysis, design evaluation and report preparation, of the aluminium alloy substructure of the MD-11 centre line engine duct assembly. • Finite element analysis of the BAe Jetstream 41, KEVLAR engine oil cooler exhaust duct.



Dowty Aerospace

• Ajax, Canada

• Stress Engineer

  • Oct 1989 - Oct 1990

  Main Program: Canadair CL-601, CL601 RJ and De Havilland Canada DHC-8 Task: Landing Gear • Amend the existing Canadair CL-601 Landing Gear Static and Fatigue analysis, to cover additional load cases and dynamics loading, to accommodate the Joint Airworthiness Requirements. • Analysis of a proposed Tail Gear design for the McDonnell Douglas/Bell LHX helicopter. • Analysis for the Canadair CL-601 Regional Jet Landing Gear Uplocks and other associated components. Determining applied loads, fatigue spectrum and completing the strength and fatigue analysis and the verification of the fatigue test spectrum. • Strength and fatigue calculations on manufacturing defects on the CL-601 and DHC-8 undercarriage assemblies. Show less



Hawker de Havilland

• Bankstown, Australia

• Engineer

  • Jan 1979 - Jul 1989

  Main Program: Sikorsky S-70A-9 Blackhawk Task: Liaison/Production Support • Project/Liaison Engineer Australian Blackhawk helicopter assembly project. • Seconded to Auspace to work on the structural and thermal analysis of an experimental space telescope. • Investigation of landing gear and flight control systems defects on military aircraft. • Australian Air Force Basic Pilot Trainer Aircraft Project - various tasks including involvement in the wing test and control of documents and drawings for the wing and undercarriage designs. January 1979 – December 1984 Cadet Engineer • Engineering Trainee to undertake a part-time engineering degree while gaining varied industrial experience. This included being apprenticed as a Ground Engineer Engines. Show less