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 LIST OF PUBLICATIONS – L. MOLENT (Sept 20)

Journal Publications:

  1. Molent L. and Dixon B, The airframe metal fatigue problem space. J Terraspace Science and Technology, 2020: 12 (1); 1-7.
  2. Main B, Molent L, Singh R and Barter S. Fatigue crack growth lessons from thirty-five years of the Royal Australian Air Force F/A-18 A/B Hornet Aircraft Structural Integrity Program, Fatigue 2020; 133:.
  3. Molent L and Singh R. Using the lead crack framework to reduce durability test duration, Aeronautical Journal 2020; 124 – 1276: 814-820. doi:10.1017/aer.2019.73,.
  4. Molent L and Dixon B. (Review Paper) Airframe metal fatigue revisited, J Fatigue 2020;131:.
  5. Molent L and Haddad A, A critical review of available composite damage growth test data under fatigue loading and implications for aircraft sustainment, Composites Struct 2020; 232: 111568.
  6. Main B., Evans R., Walker K, Yu X and Molent L. Lessons from a fatigue prediction challenge for an aircraft wing shear tie post, Journal of Fatigue 2019; 123:53-65.
  7. Wanhill RJH, Goldsmith N and Molent L., Quantitative fractography of fatigue and an illustrative case study, Engineering Failure Analysis, 2019; 19: 426-435.
  8. Molent L, Dixon B, Barter SA and Swanton G. Outcomes from the fatigue testing of seventeen centre fuselage structures, Fatigue 111C (2018) pp. 220-232.
  9. Molent L and Mau V.T., Verification of an airframe fatigue life monitoring system using ex-service structure, Eng Fail Analysis, 2017; 83: 207-219.
  10. White P., Mongru D. and Molent L., A Crack Growth Based Individual Aircraft Monitoring Method Utilizing a Damage Metric, Structural Health Monitoring, 2018; 17(5): 1178-1191.
  11. Molent L, Spagnoli A, Carpinteri A and Jones R. Using the lead crack concept and fractal geometry for fatigue lifing of metallic structural components, Fatigue 2017; 102C:214-220.
  12. Molent L. and Forrester C., The lead crack concept applied to defect growth in aircraft composite structures, Composite Structures 2017; 166:22-26.
  13. Molent L, Spagnoli A, Carpinteri A & Jones R. Fractals and the lead crack airframe lifing framework, Structural Integrity Procedia 2 (2016) 3081-3089
  14. Dixon B, Molent L and Barter S. A study of fatigue variability in aluminium alloy 7050-T7451, Int J Fatigue 2016; 92/1: 130-146.
  15. Molent L. and Jones R., A stress versus crack growth rate investigation (aka stress – cubed rule), Int J Fatigue 2016; 87:435-443.
  16. Molent L. and Jones R. The influence of cyclic stress intensity threshold on fatigue life scatter, Int J Fatigue, 2015; 82: 748-756.
  17. Gallagher JP and Molent L. The equivalence of EPS and EIFS based on the same crack growth life data, Fatigue 2015; 80:162-170.
  18. Wanhill, R.J.H., Molent, L. and Barter, S.A., 2015, Milestone case histories in aircraft structural integrity, Reference Module in Materials Science and Materials Engineering, Elsevier Inc., 2016.
  19. Molent L. Alternative methods for derivation of safe life limits for a 7050-T7451aluminium alloy structure, Fatigue 2015; 74:55-64.
  20. Molent, L., Managing airframe fatigue from corrosion pits – a proposal, Engineering Fracture Mechanics 2015; 137: 12–25.
  21. Molent L. (Invited Review paper), A review of equivalent pre-crack sizes in aluminium alloy 7050-T7451, Fat Fract Eng Mat Struct 2014;37: 1055-74.
  22. Jones R., Molent L., Barter S., Matthews N. and Tamboli D. Supersonic particle deposition as a means for enhancing the structural integrity of aircraft structures. J. Fatigue 2014; 68:260-268.
  23. Barter, S. A. and Molent, L. Fatigue Cracking from a Corrosion Pit in an Aircraft Bulkhead. Engineering Failure Analysis 39 April 2014 155-163.
  24. Molent L. A brief history of structural fatigue testing at Fishermans Bend Australia. Advanced Materials Research Vols. 891-892 (2014) pp 106-114. doi:10.4028/www.scientific.net/AMR.891-892.106.
  25. Molent L. Managing fatigue from corrosion pits in aircraft structures. Advanced Materials Research Vols. 891-892 (2014) pp 261-266. doi:10.4028/www.scientific.net/AMR.891-892.261
  26. Molent L, Barter SA, Gordon M. and Weibler L. Pseudo fatigue testing for rapid certification to service. Advanced Materials Research Vols. 891-892 (2014) pp 1059-1064. doi:10.4028/www.scientific.net/AMR.891-892.1059
  27. Gallagher JP and Molent L. Effect of load spectra and stress magnitude on crack growth behaviour variability from typical manufacturing defects. Advanced Materials Research Vols. 891-892 (2014) pp 100-105. doi:10.4028/www.scientific.net/AMR.891-892.100.
  28. Barter S. and Molent L. Service fatigue cracking in an aircraft bulkhead exposed to a corrosive environment, Engineering Failure Analysis 34 (2013) 181–188.
  29. Jones R, Molent L and Barter S. Calculating crack growth from small discontinuities in 7050-T7451 under combat aircraft spectra. J Fatigue 2013; 55: 178-182. http://dx.doi.org/10.1016/j.ijfatigue.2013.06.009
  30. Wanhill, R, Barter, S and Molent, L.  Fracture Mechanics in Aircraft Failure Analysis: Uses and Limitations, Engineering Failure Analysis, EFA 2013; 35:33-45.
  31. Siqueira AF, Baptista CARP, Molent L. On the Determination of a Scatter Factor for Fatigue Lives Based on the Lead Crack Concept, J. Aerosp. Technol. Manag., São José dos Campos, Vol.5, No 2, pp.223-230, Apr.-Jun., 2013.
  32. Molent L, Barter S and Foster W. Verification of an individual aircraft fatigue monitoring system. J. Fatigue 2012; 43: 128-133. 10.1016/j.ijfatigue.2012.03.003.
  33. Jones R, Molent L, Walker K. Fatigue crack growth in a diverse range of materials. J. Fatigue 40 (2012) 43–50 http://dx.doi.org/10.1016/j.ijfatigue.2012.01.004;.
  34. Barter SA, Molent L, Wanhill RJH. Typical fatigue-initiating discontinuities in metallic aircraft structures, J Fatigue 2012 ; 41:11-22. doi: 10.1016/j.ijfatigue.2011.10.017.
  35. Molent L, Barter SA and Wanhill RJH. The Lead Crack Fatigue Lifing Framework, Int Fatigue; 33 (2011) 323–331.
  36. Molent L and Barter SA. The lead fatigue crack concept for aircraft structural integrity, Procedia Engineering 2 (2010) 363-377.
  37. Molent, L. Fatigue Crack growth from flaws in combat aircraft. International Journal of Fatigue 32 (2010) 639-649. 10.1016/j.ijfatigue.2009.09.002.
  38. Zhuang W., Molent L. (2010) Analytical study of fatigue crack growth in AA7050 notched specimens under spectrum loading, Engineering Fracture Mechanics, 77, 1884-1895.
  39. Zhuang W.Z., McDonald M, Phillips M and Molent L. Effective block approach for aircraft damage tolerance analyses. Journal of Aircraft  Vol. 46, No. 5, September–October 2009. DOI: 10.2514/1.42306.
  40. Molent L, Barter, S, White P and Dixon B. Damage tolerance demonstration testing for the Australian F/A-18, International Journal of Fatigue 31 (2009) 1031–1038.
  41. Barter S, Molent L, White P and Dixon B. Recent Australian Full-scale F/A-18 Fatigue Tests, Structural Integrity and Life 9 (2), 2009, pp 89-112.
  42. Barter S, Dixon B and Molent L. Assessing relative severity using single fatigue test coupons, Eng Failure Analysis, 16(3) April 2009, pp863-873.
  43. Zhuang W and Molent L, Block-by-block approaches for spectrum fatigue crack growth prediction. Engineering Fracture Mechanics 75 (2008) 4933–4947.
  44. Huynh J, Molent L and Barter S. Experimentally Derived Crack Growth Models for Different Stress Concentration Factors; J. Fatigue 2008, Vol 30/10-11 pp 1766-1786.
  45. Jones R, Molent L and Krishnapillai K. An equivalent block method for computing fatigue crack growth. J. Fatigue 2008 Vol 30/9 pp 1529-1542.
  46. Jones R, Molent L and Pitt, S. Similitude and the Paris crack growth law. J Fatigue. 2008, Vol 30/10-11 pp 1873-1880.
  47. Jones R, Molent L and Pitt, S. Understanding crack growth in fuselage lap joints. Theoretical and Applied Fracture Mechanics 2008; 49:38-50.
  48. White P, Barter S and Molent L. Observations of crack path changes caused by periodic underloads in AA7050-T7451; Int Journal of Fatigue 30 (2008),1267-1278.
  49. Tiong U.H., Jones R. and Molent L., Determination of Material Constants for Crack Size-Dependence Crack Growth Model, Materials Science Forum Vols. 561-565 (2007) pp. 2189-2192.
  50. Molent L, Barter S and Main B, Life assessment and repair of fatigue damaged high strength aluminium alloy structure using a peening rework method, Engineering Failure Analysis 15 (2008) 62-82.
  51. Molent, L., McDonald, M., Barter, S., Jones, R., Evaluation of Spectrum Fatigue Crack Growth using Variable Amplitude Data, International Journal of Fatigue (2008); 30/1; 119-137.
  52. Molent L, Barter SA, A comparison of crack growth behaviour in several full-scale airframe fatigue tests, Int J Fatigue (2007); 29: 1090-1099.
  53. Molent L. and Barter S. Crack growth behaviour in historical airframe fatigue tests, Materials Australia Vol 40/1, Jan/Feb 2007.
  54. Molent, L, Q. Sun and A. Green, Charcterisation of Equivalent Initial Flaw Sizes in 7050 aluminium alloy, J. Fatigue and Fracture of Engineering Materials and Structures 29 (2006); 916-937.
  55. Zhuang, W., Barter, S. and Molent, L., Flight-by-flight fatigue crack growth life assessment, International Journal of Fatigue 29 (2007), 1647-1657.
  56. Jones, R., Molent, L. and Pitt, S., Crack growth of physically small cracks, International Journal of Fatigue 29 (2007), 1658-1667.
  57. Molent, L, Jones, R, Barter, S and Pitt, S. Recent developments in fatigue crack growth assessment, Int J. of Fatigue,  Vol 28/12 (2006) 1759-1768.
  58. Pell R.A., Mazeika P.J. and Molent L., The comparison of complex load sequences tested at several stress levels by fractographic examination,  Journal of Engineering Failure Analysis 12/4 pp. 586-603, 2005.
  59. White P., Molent L. and Barter S.,  Interpreting fatigue test results using a probabilistic fracture approach, International Journal of Fatigue 27/7 pp752-767, 2005.
  60. Barter S., Molent L., Goldsmith N. and R. Jones. An experimental evaluation of fatigue crack growth. Journal Engineering Failure Analysis, Vol 12/1 pp 99-128, 2005.
  61. Jones R., Barter S., Molent L. and Pitt S., Crack growth at low K’s and the Frost Dugdale law, Journal Chinese Institute of Engineers, Special Issue in Honour of Professor G. C. Sih, 27, 6, 869-875, 2004.
  62. Jones R., Barter S., Molent L. and Pitt S., Crack patching: an experimental evaluation of fatigue crack growth, Composite Structures 67 (2005) pp 229-238.
  63. Jones R. and Molent L., Application of constitutive modelling and advanced repair technology to F111C aircraft, Composite Structures 66 (2004) pp 145–157.
  64. Molent L., Singh R. and Woolsey J., A method for evaluation of in-service fatigue cracks, Journal of Engineering Failure Analysis Vol 12/1 pp 13-24, 2004.
  65. Molent, L. and Aktepe, B., Review of fatigue monitoring of agile military aircraft, J. Fatigue and Fracture of Engineering Materials and Structures, 23, p767-785, Sept. 2000.
  66. Knop, M., Jones, R., Molent, L. and Wang, C. On the Glinka and Neuber methods for calculating notch tip strains under cyclic. International Journal of Fatigue 22 (9), 743-755, 2000.
  67. Jones, R., Pitt, S and Molent, L. Study of Multi-Site Damage in fuselage lap joints, Theoretical and Applied Fracture Mechanics, 32, p81-100, 1999.
  68. Molent, L. and Jones, R. Crack growth and repair of Multi-Site Damage of fuselage lap joints, Engineering Fracture Mechanics Vol. 44, No. 4, pp. 627-637, 1993.
  69. Molent, L., Bridgeford, N., Rees, D. and Jones, R. Environmental evaluation of repairs to fuselage lap joints, J. Composite Structures 21 (1992) p121-130.
  70. Molent, L., Callinan, R.J. and Jones, R. Structural aspects of the design of an all Boron/Epoxy reinforcement for the F-111 wing pivot fitting: Structural Aspects, J. Composite Structures 11 (1989) pp57-83.
  71. Jones, R., Molent, L., Baker, A.A. and Davis, M.J. Bonded repair of metallic components: Thick Sections, J. Theoretical and Applied Frac.  Mech. 9 (1988) pp 61-70.
  72. Paul, J. and Molent, L. Applications of energy density theory in cyclic plasticity,  J. Theoretical and Applied Frac.  Mech. 10 (1988) pp.43-48.

Contribution to Books:

  1. Wanhill R, Barter S and Molent L. Fatigue crack growth and lifing analyses for metallic aircraft structures and components, Springer briefs in Applied Science and Technology, the Netherlands, 2019.
  2. Barter SA, Molent L, Wanhill RJH., Typical fatigue-nucleating discontinuities in metallic aircraft structures, Aircraft Sustainment and Repair, edited by Jones R et al., Butterworth-Heinemann publications, UK, 2018.
  3. Molent L. and Jones R. Repair of Multisite Damage in civil transport aircraft: An example of the damage-tolerant design of composite repairs, Aircraft Sustainment and Repair, edited by Jones R et al., Butterworth-Heinemann publications, UK, 2018.
  4. Molent L. and Jones R. The F111C wing pivot fitting repair and its implications for the design/assessment of bonded joints and composite repairs, Aircraft Sustainment and Repair, edited by Jones R et al., Butterworth-Heinemann publications, UK, 2018.
  5. Matthews N, Molent L, Barter S and Jones R. Application of SPD to enhance the structural integrity of fuselage skins and centre barrels, Aircraft Sustainment and Repair, edited by Jones R et al., Butterworth-Heinemann publications, UK, 2018.
  6. Molent L and Barter SA. Fatigue life enhancement for metallic airframe materials, N. Eswara Prasad and R.J.H. Wanhill (eds.), Aerospace Materials and Material Technologies, Indian Institute of Metals Series, Springer Science+Business Media Singapore 2017.
  7. Molent L and Athiniotis N., 75 years of scientific accident investigation support at the Bend, DSTO monogram, DSC 1588 Jul 2016.
  8. Barter SA, Molent L. and Wanhill RJH., Fatigue Life Assessment for High Performance Metallic Airframe Structures – An Innovative Practical Approach. Structural Failure. Analysis and Prediction Methods for Aerospace Vehicles and Structures, editor: Sook-Ying H, Bentham Science Publishers, 2010.
  9. Zhuang W and Molent L, Fatigue crack growth analysis for notched specimens under flight spectrum loading. Structural Failure Analysis and Prediction Methods for Aerospace Vehicles and Structures, editor: Sook-Ying H, Bentham Science Publishers, 2010.
  10. Molent L, Barter SA. and Jones R., Some Practical Implications of Exponential Crack Growth, Multiscale Fatigue Crack Initiation and Propagation of Engineering Materials: Structural Integrity and Microstructural Worthiness, ISBN 978-1-4020-8519-2, Edited by Sih GC., Springer Press, June 2008.
  11. Molent L and Agius J. Structural health monitoring of agile military aircraft. Encyclopedia of Structural Health Monitoring, Edited by C. Boller, F Chang and Y. Fujino, John Wiley & Sons, Ltd. 2008.
  12. Jones R., Barter S., Molent L., and Pitt S., A multi-scale approach to crack growth, Chapter in the Book, Multiscaling in molecular and continuum mechanics: biology, electronics and material science, Edited by G. C. Sih, Springer, March 31, 2006.
  13. Jones, R. and Molent, L., Repair of Multi-Site Damage, In Advances in Bonded Composite Repair of Metallic Aircraft Structure, Vol. 1 edited by A. Baker, F. Rose and R. Jones, Elsevier Science Ltd, 2002.
  14. Jones R., Bridgford N., Wallace G. and Molent L. Bonded repair of Multi-site Damage, Structural         Integrity of Aging Airplanes, pp 199-213, edited by S.N. Atluri, S.G. Sampath and P. Tong, Springer Verlag, Berlin/Heidelberg, 1991.
  15. Jones, R., Molent, L., Baker, A.A. and Davis, M.J. Bonded repair of metallic components: Thick Sections, Analytical and testing methodologies for design with advanced materials, Edited by C. G. Sih et al., Amsterdam, North Holland, 1988.

Conference Papers:

  1. Molent L, Jones R and Kinloch A.J. Assessing delamination growth under cyclic loading, Proc. ICCM22, Melb., Aust. 12-16 Aug 2019.
  2. Molent L. (keynote). Management of detected aircraft in-service pitting corrosion, proc.13th Int Conf on the Mechanical Behaviour of Materials (ICM13), 11-14th Jun 2019. Melb., Aust.
  3. Molent L and Singh R., Using the lead crack concept to reduce durability test duration, Proc. AIAC18, Melb 24-26 Feb 2019. Awarded best paper.
  4. Molent L. (keynote) The in-service management of airframe fatigue nucleated form corrosion pits, Proc. NATO-RTO-AVT-303 Corrosion Management, Athens, GR, 10-12 Dec 2018.
  5. Molent L. Using the lead crack concept to reduce durability test duration, Proc. ICAS 2018 Belo Horizonte, Brasil, 10-14 Sept 2018.
  6. Molent L and Forrester C. The lead crack concept applied to defect growth in composite structures, Proc. AIAC17, Melb, 26-28 Feb 2017.
  7. Molent L, Barter S and Wanhill RJH. The decoupling of corrosion and fatigue for aircraft service life management, Proc ICAF Symposium, Helsinki, 3-5 Jun 2015.
  8. Molent L. Safe life limits for a 7050-T7451 aluminium alloy structure using initial discontinuity sizes, Proc AIAC16, Melbourne 23-24 Feb 2015.
  9. White P, Molent L, Jones S and Gordon M. History of tracking fatigue of the RAAF F/A-18 Hornet, AIAC16, Melbourne 23-24 Feb 2015.
  10. Molent L. The FINAL experience – Managing airworthiness by testing retired structure. Proc of Continuing Airworthiness of Aging Aircraft Systems (AVT-222-RWS-019), Brussels 13-15 Oct 2014.
  11. Molent L and Athiniotis N. 75 years of scientific accident investigation support at the Bend, Proc ISASI, Adelaide 13-16 Oct 2014.
  12. Barter S. and Molent L*. Service fatigue cracking in an aircraft bulkhead exposed to a corrosive environment, Proceedings for the 8th International Conference on Structural Integrity and Fracture, Melb 11-12 Jul 2013.
  13. Molent, L. Managing fatigue from corrosion pits – a proposal. Proc. AIAC15, Melb 25-28 Feb 2013.
  14. Barter, S. and Molent L. Investigation of an in-service crack subjected to aerodynamic buffet and manoeuvre loads and exposed to a corrosive environment. Proc. 28th International Congress Of The Aeronautical Sciences, Brisbane 23-28 Sept 2012.
  15. Wanhill RJH, Molent L, Barter SA. Fracture mechanics in aircraft failure analysis: Uses and limitations, Proc Fifth Int Conf on Engineering Failure Analysis, The Hague NL, 1-4 July 2012.
  16. Molent L,  Barter S and Foster W. Verification of an individual aircraft fatigue monitoring system, proc of USAF AISP Conference  Nov 29 – 1 Dec 2011, San Antonio, USA.
  17. Molent L,  Barter S,  Kloeden R. and Needham G. DSTO testing in support of the sustainability of the Hornet’s structural integrity as part of the SRP. Aircraft Airworthiness and Sustainment (Australia), Brisbane Qld, 26-28 July 2011.
  18. Barter S.A., Molent L. and Wanhill R.J.H. Fatigue-initiating discontinuities in aircraft structures. Fatigue & Defects Symposium, Trondheim, 23-25 May 2011.
  19. Barter S.A., Molent L. and Wanhill R.J.H. Fatigue-initiating discontinuities in aircraft structures. 14th Australian International Aerospace Congress, Melbourne 28th Feb – 3rd Mar 2011.
  20. Barter, SA, Molent L and Robertson L. Using in-service F/A-18 A / B aircraft fatigue cracking as disclosed by teardown to refine fleet life limits. Proc USAF ASIP Conference, Jacksonville, FL, 1-3 Dec 2009.
  21. Barter SA, Molent L and Wanhill RJH, Marker loads for quantitative fractography of fatigue cracks in aerospace alloys. Proc ICAF 2009, Rotterdam 27-29 May 2009. Awarded best paper.
  22. L. Molent, B. Dixon, S. Barter, P. White, T. Mills, K. Maxfield, G. Swanton and SQNLDR B. Main. Enhanced teardown of ex-service F/A-18A/B/C/D centre fuselages. Proc ICAF 2009, Rotterdam 27-29 May 2009.
  23. L. Molent, B. Dixon, S. Barter, P. White, T. Mills, K. Maxfield, G. Swanton and SQNLDR B. Main. The F/A-18 FINAL fatigue testing program. Proc AIAC13, Melbourne, 10-11 Mar 2009.
  24. Zhuang W. Z., McDonald M., Phillips M.  and Molent L. Applications of effective block approach for aircraft damage tolerance analyses; Proc AIAC13, Melbourne, 10-11 Mar 2009.
  25. Molent, L, Boykett, R and Walker K, Maintaining Reliability and Availability in a Sole Operator Environment, RTO-MP-AVT-157, Montreal, Canada, 13-16 Oct 2008.
  26. Boykett R, Walker K and Molent L. Sole operator support for the RAAF F-111 fleet. 11th Joint NASA/FAA/DOD Conference on Aging Aircraft, Phoenix, 21-24 Mar 2008.
  27. Zhuang W and Molent L. Block-by-block approach for spectrum fatigue crack growth prediction. The Eighth International Conference on Fundamentals of Fracture (ICFF VIII) Hong Kong & Guangzhou, China. 3-7 January 2008.
  28. Molent*, L., Barter, S., McDonald, M. and Jones, R. Spectrum fatigue crack growth evaluation using variable amplitude data, Proc. 12th Aust Int Aerospace Congress, Melbourne 19-22 Mar 2007.
  29. Tiong U.H., Jones  R. and Molent L., Damage tolerance analysis of a helicopter component,  Proceedings 1st International Conference on Damage Tolerance  Assessment of Aircraft Structure, Delft, The Netherlands, September  25th-28th, 2007.
  30. Molent* L., Barter S.A, White P. and Dixon B., Damage tolerance demonstration testing for the Australian F/A-18, Proceedings 1st International Conference on Damage Tolerance  Assessment of Aircraft Structure, Delft, The Netherlands, September  25th-28th, 2007.
  31. Molent L, McDonald M and Barter SA. Using full-scale fatigue testing crack growth results to life aircraft fleets, proc L. Molent, M. McDonald, S. Barter  24th ICAF Symposium – Naples, 16-18 May 2007.
  32. Tiong U.H., Jones R., Molent L. and Huynh J., Analysis of short fatigue crack growth in the presence of multi-site damage, Proc. Int. Conf. on Structural Integrity and Failure, Sydney 27-29 Sept 2006.
  33. Jones R., Wallbrink C., Pitt S. and Molent L., A Multi-scale approach to crack growth, Proc Mesomechanics 2006: Multiscale Behaviour of Materials and Structures: Analytical, Numerical and Experimental Simulation, Porto, Portugal, 19-22 July 2006. To appear in Journal of Theoretical and Applied Fracture Mechanics.
  34. Zhuang W., Barter S. and Molent L., Flight-by-flight fatigue crack growth life assessment. Proceedings International Conference on Fatigue Damage of Structural Materials VI, Hyannis, USA, September 2006.
  35. Jones R., Molent L., and Pitt S., Crack growth of physically small cracks, Proceedings International Conference on Fatigue Damage of Structural Materials VI, Hyannis, USA, September 2006.
  36. Molent* L. and Barter S.A., Crack growth comparison in several full-scale airframe fatigue tests, Proc. Int. Conf. on Structural Integrity and Failure, Sydney 27-29 Sept 2006.
  37. Jones R., Molent L., Pitt S., and Siores E., Recent developments in fatigue crack growth modelling, Proceedings 16th European Conference on Fracture, Greece, July 2006.  To appear in Journal of Theoretical and Applied Fracture Mechanics.
  38. Molent* L. and Barter S.A., A comparison of crack growth behaviour in several full-scale airframe fatigue tests, proc. Int. Fatigue Congress 2006, Atlanta, May 15-19, 2006.
  39. Barter, S, McDonald, M and Molent L, Fleet fatigue life interpretation from full-scale and coupon fatigue tests – a simplified approach, USAF ASIP Conference, Memphis, 29 Nov – 1 Dec 2005.
  40. Molent* L, Dixon B, Barter S, Medved J. and Nguyen Q., The FINAL program of enhanced teardown for a fighter aircraft, proc. ICAF 2005 Hamburg, Jun 8-10, 2005.
  41. Molent* L., Barter S.A, White P. and Dixon B., Summary of recent Australian full-scale F/A-18 fatigue tests, proc Aust Intern Aerospace Conference, Melb 13-17 March 2005.
  42. Dixon, B., Molent, L. and Barter, S.A, The FINAL program of enhanced teardown for agile aircraft structures, pro. of  8th NASA/FAA/DOD Conference on Aging Aircraft, Palm Springs, 31 Jan – 3 Feb 2005.
  43. Molent L., Barter S., Pitt S. and Jones R., Developments in fatigue life assessment, proc. of Structural Health Monitoring Workshop, Monash University, Melbourne, 16 & 17 December 2004.
  44. Molent*, L., Dixon, B. and Barter, S., Flaw IdeNtification through the Application of Loading, proc of  Structural Integrity and Fracture Conference 2004, Brisbane, 26-29 Sept 2004.
  45. Barter S. A., Molent L., Robertson P., Thompson S., Fox G. and Kimmins G., Field investigation of the accident involving an Ilyushin IL-76 transport aircraft in East Timor in 2002, proc. of ISASI 2004, Gold Coast, Sept 2004.
  46. Jones, R. and Molent L., The F-111 WPF repair: A Case Study, International Conf on Composite Structures, Melbourne, 17-19 Nov 2003.
  47. Pell R.A., Mazeika P.J. and Molent L., The comparison of complex load sequences tested at several stress levels by fractographic examination, Proc. of International Committee on Aeronautical Fatigue Conference, Lucerne Switzerland, 7-9 May 2003.
  48. Barter, S, Molent, L, Landry, N, Klose, P, and White, P., Overview of the F/A-18 aft fuselage combined manoeuvre and dynamic buffet fatigue and residual strength testing, proc. Australian International Aerospace Congress, Brisbane Aust., July 29 – 1 Aug 2003.
  49. Molent*, L., Considering the role of health monitoring in fixed wing airframe  HUMS, Proc. HUMS2003, Melbourne, Australia, 17 –18 Feb 2003.
  50. Molent*, L., Barter, S., White, P. and Conser, D., Overview of the F/A-18 Aft fuselage combined manoeuvre and dynamic buffet fatigue Test, proc of USAF Structural Integrity Program Conference, Savannah, Georgia, 10-12 Dec 2002.
  51. White, P., Barter, S. and Molent, L, Probabilistic fracture prediction based on aircraft specific fatigue test data, proc. 6th Joint FAA/DoD/NASA Aging Aircraft Conference – San Diego, Sept.16-19, 2002.
  52. Molent*, L., F/A-18 collaborative fatigue testing,  The 2002 Sir Lawrence Wackett Lecture, Melbourne Australia, Oct 2002.
  53. Simpson, D.L., Landry, N., Roussel, J., Molent, L., Graham, A.D., and Schmidt, N., The Canadian and Australian F/A-18 International Follow-On Structural Test Project, Proc. ICAS 2002 Congress, Toronto, Canada Sept. 2002.
  54. Molent*, L., White, P. and Harman, A., Bounding structural durability due to buffet induced loading, proc. of 9th Aust. Intern. Aerospace Congress, Canberra, 4-8 March 2001.
  55. Molent*, L. and S. Inan, Specifications for an unified strain and flight parameter based aircraft fatigue usage monitoring system, proc of DSTO HUMS Conference, DSTO-GD-0262, Melbourne 19-20 Feb., 2001.
  56. Barter S., Molent* L, Sharp K. and Clark G.,  Repair and life assessment of critical fatigue damaged aluminium alloy structure using a peening rework method, proc of USAF Structural Integrity Program Conference, San Antonio, TX, 5-7 Dec 2000.
  57. Aktepe, B*., Molent, L., Graham, D. and Conser, D., Buffet loads and structural redundancy considerations in vertical tail fatigue monitoring programs, Proc. Inter. Aerospace Congress, Sept 13-14 1999, Adelaide.
  58. Aktepe, B*. and Molent, L., Management of airframe fatigue through individual aircraft loads monitoring programs, Proc. Inter. Aerospace Congress, Sept 13-14 1999, Adelaide.
  59. Molent, L*., Proposed specifications for a ununified strain and flight parameter based aircraft fatigue usage monitoring system, proc of USAF Structural Integrity Program Conference, San Antonio, TX, 1-3 Dec 1998.
  60. Molent, L*., A unified approach to fatigue usage monitoring of fighter aircraft based on F/A-18 experience, Proc of ICAS98, Melbourne, 13-18 Sept 1998..
  61. Molent, L*., A review of a strain and flight parameter data based aircraft fatigue usage monitoring system, proc of USAF Structural Integrity Program Conference, San Antonio, TX, 3-5 Dec 1996.
  62. Walker, K. and Molent, L. Corrtest: A computer program for correlating and validating separate but related sets of fatigue data in range mean pair form, Proc. ICAF Conference, Melbourne, 3-5 May 1995.
  63. Molent*, L., Structural Investigations into the Collapse of the Wing Leading Edges of Orion P-3C, proc. PICAST2 – AAC6, Melbourne 20-23 March 1995.
  64. Walker, K. and Molent, L. Development of an automated procedure for correlation of two sets of range mean pair fatigue sensor data, Proc. of USAF   Structural Integrity Program Conference, San Antonio, TX, 6 – 8th. Dec. 1994.
  65. Jones, R., Molent, L., Paul, J., Saunders, T. and Chui, W.K., Development of a Composite Repair and Associated Inspection Intervals for the F-111C Stiffener Runout Region, proc. FAA/NASA International Symposium on Advanced Structural Integrity for Airframe Durability and Damage Tolerance,  Hampton VA, USA, May 1994. (NASA Conference Pub 3274, Pt 1, pp 339-351).
  66. Molent*, L., ARL Analysis of the Crash of P3-C A9-754, presented at P-3 International  Operators Support Conference,  Marrietta, Georgia, USA, 20-22nd Oct. 1992.
  67. Jones, R., Molent, L., Rees, D., Kaye, R. and Rowlands, D., An Experimental Study of Multi-Site Damage and Repairs, Proc. Aging Commuter Aircraft Conference, Canberra, 4-6 Aug. 1992.
  68. Molent*, L., Composite Repair of Aircraft Structures –  The Australian Experience, proc. USAF   Structural Integrity Program Conference, San Antonio, TX, 2 – 5th. Dec. 1991.
  69. Molent*, L., Boron Fibre Crack Repair Techniques, presented at C130 Hercules Life Extension Initiatives (HLEI) Conference, 28 – 31st. Oct. 1991, Atlanta Georgia, USA.
  70. Molent*, L., Composite Repair of Aircraft Structures, Presented at AIAA International Conference, Feb. 12-14th 1991, Los Angeles, USA.
  71. Jones, R., Bridgford, N., Wallace, G. and Molent, L., Bonded Repair of Multi-Site Damage, proceedings, International Symposium on ‘Structural Integrity of Aging Airplanes’, Atlanta, USA, March 1990.
  72. Jones, R., Heller, M. and Molent, L., Thoughts on Energy Density, Fracture and Thermal Emission Analysis,  Proc. Int. Sym. on Mechanics and Physics of Energy Density, edit. by G. Gdoutous and G.C. Sih, Martinus Nijheff Publishers, Dordrecht Netherlands 1989.

University and other Papers

  1. Liao M, Jones K, Wolfgang B, Molent L et al., Continuing airworthiness of aging systems, NATO STO technical report, TR-AVT-275, Aug 2019.
  2. Molent, L., DSTO and Aircraft Accident Support, Touchdown Issue 1, The Australian Navy Aviation Safety and Information Magazine,  April 2003.
  3. Molent, L. and Naylor, L., HMF618, Emergency Planning and Management – Part 2, Swinburne University of Technology, Hawthorn, Victoria, 2000.
  4. Molent, L., F/A-18 Service Life Bulletin Number 3, Aircraft Structural Life Limits for Flight, Catapults and Arrestments,  NAVAIR Instruction, NAVGRAM 24th June 1991.
  5. Partridge, C., Williams, J.F., Jones, R., Molent, L. and Waechter, Temperature and Dissipated Energy Effects During the Monotonic Stressing of Metals – Part 2”, Uni. Of Melbourne, Dept. of Mech. and Manufacturing Engineering, Int. Rep. SM/1/88, Mar 1988.

DST SERIES

  1. Molent L. General fatigue lifing of metallic aircraft structures, DST-Group-TBD, in press.
  2. Dixon B, Molent L and Barter S. A study of fatigue variability in aluminium alloy 7050-T7451, DST Group-RR-0425, Dec 2015.
  3. Molent L. and Mau VT. Verification of the RAAF F/A-18A/B Airframe Service Life Monitoring Program Using RAAF Ex-service Centre Barrels, DSTO-RR-0414, May 2015.
  4. Molent L. and Swanton G. The DSTO Contribution to the Fatigue Life Reassessment of the RAAF F/A-18 Hornet Centre Barrel Structure, DSTO-TR-3062, Dec 2014.
  5. Loader C,  Crawford BR,  Sharp K and Molent L. A Proposal for the Management of Detected Pitting Corrosion for the F/A-18 Hornet,  DSTO-TR-2976, Apr 14.
  6. Molent L. and Sun Q. Analysis of F/A-18 Hornet Crack Growth Compendium Data. DSTO-RR-0378, Feb 2012.
  7. Mills T. and Molent L., The RAAF F/A-18 Mission Severity Monitoring Program V2, DSTO-TR-2601, Sept 2011.
  8. Molent, L and Sun, Q. The Compendium of F/A-18 Hornet Crack Growth Data Version II: Part 1. DSTO-TR-2488, Nov 2010.
  9. Molent L, Barter SA, and Wanhill RJH. The Lead Crack Fatigue Lifing Framework, DSTO-RR-0353, Apr 2010.
  10. Jones, R and Molent L. Critical review of the generalised Frost-Dugdale approach to crack growth in F/A-18 Hornet structural materials, DSTO-RR-0350, March 2010.
  11. Maxfield K., Dixon B., Molent L. and Barter S. Flaw Identification through the Application of Loads: Test and Teardown of the F/A-18A/B Centre Barrel from FT46, DSTO-TR-2377, Jan 2010.
  12.  Molent L, Toman S and Sherman D. DSTO accident investigation report Caribou damaged on landing in Papua New Guinea 05 September 2008. DSTO-TR-2295, Jun 2009.
  13. Dixon B. and Molent L. Comparison of the FT55 and ST16 Full-Scale Fatigue Test Spectra Severities. DSTO-TN-0861, July 2008.
  14. Molent, L, Mills T and McDonald M. F-35 Airframe Systems Description Document – Issue 1. DSTO-TR-2214, Nov 2008.
  15. Dixon, B. and Molent, L., “Fatigue Test of a Heat Damaged USN F/A- 18 Centre Barrel”, DSTO-TR-2199, Oct. 2008.
  16. Huynh J and Molent L. Application of the effective block approach to Al7050-T7451 coupon results tested under seven different F/A-18 spectra, DSTO-TR-2179, Sept 2008.
  17. Zhuang W., Boykett R., Phillips M. and Molent L. Effective Block Approach for Damage Tolerance Analyses of F-111 D/F Model Wing Structures. DSTO-TR-2124, May 2008.
  18. Zhuang W. and Molent L., Fatigue Life Assessment of the F/A-18 A/B Bootstrap Fitting, DSTO-TR-2075, Nov 2007.
  19. Huynh J and Molent L, The Fractographical Examination of F/A-18 Aluminium Alloy 7050-T7451 Bulkhead Representative Coupons Tested Under the ST16 and FT245 Spectra, DSTO-TR-2010, Jul 2007.
  20. Huynh J, Molent L and Barter S, Fatigue Crack Growth Predictions for 7050 Aluminium Alloy with Different Stress Concentration Factors, DSTO-RR-0330, Jul 2007.
  21. Molent, L. F/A-18 IFOSTP FT46 Final Test Report, DSTO-TR-1983, Apr 2007.
  22. A. Mabanta, G. Bain, R. Eustace, D. Forrester, S. Galea, O. Levinski, L. Molent and R. Vodicka, Air Vehicle Technology Risk and Performance Assessment of F-35 Aircraft 2005, DSTO-CR-2006-0086, Apr 2006.
  23. M. McDonald, L. Molent and A. Green, Assessment of Fatigue Crack Growth Prediction Models for F/A-18 Representative Spectra and Material, DSTO-RR-0312, Apr 2006.
  24. L. Molent and Q. Sun Distribution of Equivalent Pre-Crack Size in 7050 Aluminium Alloy, DSTO-TR-1700, March 2006.
  25. W. Zhuang, S.A. Barter, M. McDonald and  L. Molent, Fatigue Crack Growth Life Assessment of the F/A-18 Aft Fuselage Frames (Y645 and Y657), DSTO-TR-1826, Feb 2006.
  26. Molent, L., The History of Structural Fatigue Testing at Fishermans Bend Australia, DSTO-TR-1773, Oct 2005.
  27. Dixon, B., Molent, L. Barter, S.A and Mau V., Flaw Identification through the Application of Loads:  Teardown of the Centre Barrel from USN F/A-18D buno 163507, DSTO-TR-1740, Jul 2005.
  28. Dixon, B., Molent, L. Barter, S.A and Mau V., Flaw Identification through the Application of Loads:  Teardown of the Centre Barrel from USN F/A-18D buno 163510, DSTP-TR-1980, Apr 2005.
  29. L. Molent,Q. Sun and A.J. Green, The F/A-18 Fatigue Crack Growth Data Compendium, DSTO-TR-1677, Feb 2005.
  30. Dixon, B., Molent, L. Barter, S.A and Mau V., Flaw Identification through the Application of Loads:  Teardown of the Centre Barrel from CF-18 188747, DSTO-TR-1660, Dec 2004. CD only
  31. Molent, L.,  Barter S.A. and Green, A.J., Comparison of Two F/A-18 Aluminium Alloy 7050-T7451 Bulkhead Coupon Fatigue Tests, DSTO-TR-1646, Nov 2004.
  32. Huynh, J., Molent, L. and Barter, S., F/A-18 Inner Wing Lifing Investigation, DSTO-TR-1641, Nov 2004.
  33. Pell R.A., Molent L. and Green A.  The fractographical examination of F/A-18 aluminium alloy 7050-T7451 bulkhead representative coupons tested under two service spectra and two stress levels, DSTO-TR-1629, Oct 2004.
  34. McDonald, M. and Molent, L., Fatigue Assessment of the F/A-18 Horizontal Stabilator Spindle, DSTO-TR-1620, Oct 2004.
  35. Krieser, R. and Molent, L. (editors), A Record of the Australian Mirage Wing Fatigue Test, DSTO-TR-1561, Mar 2004.
  36. Pell R.A., Molent L., and Green,  A.J., “The Fractographical Comparison of F/A-18 Aluminium Alloy 7050-T7451 Bulkhead Representative Coupons Tested Under Two Fatigue Load Spectra at Several Stress Levels”, DSTO-TR-1547, Feb 2004.
  37. Ghidella, J.R., Molent, L. and Madley, W.B., “A Comprehensive Guide to the Fatigue Damage Assessment Computer Program CI89”, DSTO-TR-1506, Oct 2003.
  38. Molent, L. and Mau, V.T., “Development of New F/A-18 MSDRS Wing Root Strain Data Integrity Checks”, DSTO-TR-1518, Oct 2003.
  39. Huynh, J., Molent, L. and Barter, S., “Fatigue Life Analysis of the F/A-18 Wing Fold”, DSTO-TR-1484, Sept 2003.
  40. Molent, L., Mills, T. and Pell, R., “F/A-18 FS488 Bulkhead Fatigue Coupon Test Program – Part 2”, DSTO-TR-1464, July 2003.
  41. Mills, A., Amaratunga, R., Barter, S. and Molent, L., “Fatigue Life Estimation of the F/A-18 Bootstrap”, DSTO-TR-1463, July 2003.
  42. Dixon, B. and Molent, L., “Ex-Service F/A-18 Centre Barrel Fatigue Flaw Identification Test Plan, DSTO-TR-1426, May 2003.
  43. Molent, L., Landry, N. and Trezise, S., Results of the Residual Strength Test of the F/A-18 Aft Fuselage Fatigue Test Article FT46, DSTO-TR-1424, May 2003.
  44. Hughes, D., Kekoc, V.,  Trezise, S., White, P. and Molent, L., “Derivation of Loads for the Residual Strength Test of the F/A-18 Aft Fuselage Fatigue Test Article FT46”, DSTO-TR-1427, Apr 2003.
  45. Molent, L. and Barter, S., “Wreckage Examination of the IL-76 Aircraft Crash at Baucau East Timor”, DSTO-TR-1423, Apr 2003.
  46. Molent, L. and Mau, V.T., “Validation Against Coupon Test Results of the Fatigue Damage Model CI89 for F/A-18 aft Fuselage and Empennage Spectra”, DSTO-TR- 1292, Mar 2002.
  47. Molent, L., Stimson, M., Dickinson, T., Inan, S., Whiteroad, I. and Anderson, I., “F/A-18 Structural Refurbishment Project Assessment Activity – Volumes 2, DSTO-TN- 0413, Mar 2002
  48. Molent, L., Stimson, M., Dickinson, T., Inan, S., Whiteroad, I. and Anderson, I., “F/A-18 Structural Refurbishment Project Assessment Activity – Volumes 1, DSTO-TR- 1238, Mar 2002.
  49. Molent, L and Mills, T., “Analytical Comparison of F/A-18 IFOSTP Wing Spectra”, DSTO-TR-1245, Nov 2001.
  50. Molent, L, Pilalis, J., Finney, J.M., Madley, W.B., and White, P.D., “IFOSTP Coupon Fatigue Test Comparisons of Canadian and Australian F/A-18 Pre-LEX Fence Usage”, DSTO-TR-1228, Oct 2001.
  51. Molent, L., Barter, S., Lombardo, D., Rebbechi, B. and Forrester, D., “Post-Accident Airframe Investigation of Squirrel N22-011”, DSTO-TR-1196, Aug 2001.
  52. Molent, L. and S. Inan, “Recommendations for an Individual Aircraft Tracking System for an Agile Fighter Type Aircraft”, DSTO-TR-1102, Feb. 2001.
  53. Dickinson, T. and Molent, L., “Development of a RAAF F/A-18 “All-Time” Usage Spectrum for the Wing Fold”, DSTO-TR-1069, Nov 2000.
  54. Dickinson, T. and Molent, L., “Managing F/A-18 Fatigue Damage Using Operational Parameters”, DSTO-TR-0985, May 2000.
  55. Molent, L. and Gadd, J., “A Review of RAAF F/A-18 Aircraft Fatigue Data Analysis System (AFDAS)”, DSTO-TR-0942, April 2000.
  56. Dickinson, T. and Molent, L., “F/A-18 Left to Right Wing-Root Strain Variability”, DSTO-TR-0943, March 2000.
  57. Molent, L., “Recommendations for a New RAAF F/A-18 Aircraft  Service Life Monitoring Program”, DSTO-RR-0169, Feb 2000.
  58. Molent, L., Ogden, R. and Pell, R., “F/A-18 FS488 Bulkhead Fatigue Coupon Test Program”, DSTO-TR-0941, Feb 2000.
  59. Dickinson, T. and Molent, L., “Validation of Fatigue Damage Models used for F/A-18 Life Assessment using Fatigue Coupon Test Results”, DSTO-TR-0940, Feb 2000.
  60. Aktepe, B., Hewitt, K.P., Molent, L. and Ogden, R.W., “Validation of RAAF F/A-18 Analytical Fatigue Strain Sensor Calibration Techniques Using An Aircraft Ground Calibration Procedure”, DSTO-TR-0641, Jan 2000.
  61. Barylko, A., Beer, C., Ignjatovic, M. and Molent, L., “RAAF F/A-18 Vertical Tail Fatigue Life Estimates Using SAFE V200”, DSTO-TR-923, Jan 2000.
  62. Chapman, P., Hewitt, K. and Molent, L., “A Critical Review of the F/A-18 Vertical Tail Fatigue Tracking Process”, DSTO-TR-0642, Jan 2000.
  63. Fieldhouse, I., Foster, W., Gadd, J., Ghidella, J., Graham, D., Hewitt, K., Houstan, M., Madley, W., Molent, L., Mongru, D., Ogden, R., Ritchie, J., Stimson, M., Swanton, G. and Turner, J., “Interim Structural Life Prediction for the F/A-18 under RAAF Usage”, DSTO-TR-0760, Jan 2000.
  64. Hewitt, K. P. & Molent, L. “An Investigation Into F/A-18 Vertical Tail Life Improvement Factors”, DSTO-TR-0922, Dec 1999.
  65. Molent, L. and Ogden, R., “Preliminary Review of the Structural Appraisal of Fatigue Effects (SAFE) Program, Version 200”, DSTO-TR-0886, October 1999.
  66. Molent, L. and Barter, S.A., “Report on DSTO Investigations into the Incident Involving F-111G A8-291”, DSTO-TR-0846, July 1999.
  67. Barter, S.A. and Molent, L., Trial of Global Positioning System Based Field Wreckage Plotting and Analysis Equipment Using Data from a USMC F/A-18 Aircraft Accident, DSTO-TR-0828, Jun 1999.
  68. Molent, L. and Barter, S.A., “Preliminary Report on DSTO Investigations into the Incident Involving F-111G A8-291”, DSTO-DDP-0325, May 1999.
  69. Jones, R., Knopp, M., Price, J. and Molent, L., Stress and Strain Estimation at Notches in Aircraft Structures, DSTO-GD-0196, COE-SM-98-01, Oct. 1998.
  70. Ayling, J. and Molent, L., “An Investigation into the Program FAMS (Fatigue Analysis of Metallic Structures)”, DSTO-TR-0681, Jun 1998.
  71. Molent, L. and Ogden, R. (editors), “Review of RAAF F/A-18 “Structural Appraisal of Fatigue Effects” (SAFE) Version 112, Volume 1: Detailed Review”, DSTO-TR-0381/1, Jan 1998.
  72. Graham, D. and Molent, L., “Review of RAAF F/A-18 “Structural Appraisal of Fatigue Effects” (SAFE) Version 112, Volume 3: Overview”, DSTO-TR-0381/3, Nov 1997.
  73. Guan Ooi, Y., Ogden, R.W. and Molent, L., “Validation of an Analytical Technique for Scaling of F/A-18 Vertical Tail strain Sensors”, DSTO-TR-0539, Jun 1997.
  74. Molent, L., Structural and Flight Trial Analysis in Support of AS-350 Squirrel Helicopter Tail Boom Buckling, DSTO-TR-0206, Jul 1995.
  75. Molent, L., Walker, K. and Ogden, R.W., A Data Screening Technique for AFDAS, DSTO-TR-0204, Jul 1995.
  76. Molent, L., Ogden, R.W. and Guan Ooi, Y., “Development of Analytical Techniques for Calibration of F/A-18 Horizontal Stabilator and Wing Fold Strain Sensors”, DSTO-TR-0205, Aug 95.
  77. Molent, L., Ogden, R.W. and Guan Ooi, Y., Development of Analytical Techniques for Calibration of F/A-18 Horizontal Stabilator and Wing Fold Strain Sensors, DSTO-TR-0205, Aug 95.
  78. Hillen, L., Kepert, J.L. and Molent, L., Missile Warhead Trials 1992, DSTO-TR-0092,  Nov 1994.
  79. Molent, L., Visit Report to LASC to Discuss the Analysis of the Accident Involving Orion A9-754, DSTO-OSR-0004, August 1994.
  80. Molent, L., Further Structural Investigations Into The Collapse of the Wing Leading Edges of Orion A9-754, DSTO-TR-0008, May 1994.
  81. Athiniotis, N, Sharp, P.K., Molent, L, et al.  Examination of Components from Crashed F-111C Aircraft A8-127, ARL-Tech R- 61, Feb 1994.
  82. Molent, L., Enke, N., Wallace, G. and Jones, R., Thermomechanical analysis of bonded repaired skin splice joint specimens, ARL-TECH-R-24, Jan 1994.
  83. Molent, L. and Swanton, G., “A Parametric Survey of Cracking in the RAAF’s F-111C WPF Stiffeners”, ARL-TECH-R-55, Feb 1994.
  84. Molent, L.,  Aktepe, B. and Polanco, F., “F/A-18 Airframe Fatigue Data Analysis System Validation”, ARL-Tech-R-54, Jan. 1994.
  85. Rees, D. and Molent, “Analysis Of Candidate Bonded Repairs For Cracks In The Weep Holes Of USAF C141 Aircraft”, ARLTech Note- 62, Dec 1993.
  86. Molent, L. and Barter, S., “Wreckage Examination of Kiowa Aircraft A17-044”, ARL-TECH-R-38, May ’93.
  87. Molent, L. and Swanton, G., “F-111 Fuel Flow Hole No.13 Strain Surveys”, ARL-TN-33, June ’93.
  88. Molent, L. and Patterson, A.K., “Strain Survey of F-111C Aircraft A8-113”, ARL-STRUC-TM-585, Aug ’92.
  89. Molent, L., Kepert, J.L., Sharp, P.K. and Lamb, S.R., “Wreckage Examination of F/A-18B Aircraft A21-106”, ARL-APP-R-87, Sept ’92.
  90. Molent, L., “A Report on an Attachment to the Headquarters Naval Air Systems Command – Sept 90 to Dec 91”, ARL-STRUC-TM-551, May 1992.
  91. Rees, D., Molent, L. and Jones, R., “Damage Tolerance Assessment of Boron/Epoxy Repairs to Fuselage Lap Joints”, ARL-STRUC-R-449, Aug ’92.
  92. Athiniotos, N, Sharp, P.K., Barter, S.A., Molent, L., Stimson, M.G., Callinan, R., Clark, G. and Kepert, J.L., “Wreckage Examination of Boeing 707-338C Aircraft A20-103”, ARL-Applied Report 86, Jul. ’92.
  93. Keays, R.H., Molent, L. and Graham, D.A., “F-111 Wing Pivot Fitting Finite Element Investigation of Various Reworks of Fuel Flow Hole No:13”, ARL-STRUC-TM-557, Sept ’92.
  94. Molent, L. and J.D. Roberts, “Bonded Repair Application to the Boeing 747-400 Pressure Test Article – August 1990”, ARL-STR-TM-573, Mar ’92.
  95. Molent, L. and Davis, M., “Report on Visit to RSAF December 1989”, ARL-STR-TM-528, Jan ’90.
  96. Molent, L., Wallace, G. and Currie, A., “Crack Growth and Repair of Multi-site Damage of Fuselage Lap Joints”, ARL-STR-TM-534, Feb. ’90.
  97. Molent, L., “Analysis of F-111A Sealant Injection Holes”, ARL-STR­-TM-502, Feb ’89.
  98. Molent, L. and Lombardo, D., “An Investigation into Various Reworks of a F-111 Stiffener Replica Specimen using the Thermoelastic Effect”, ARL-STR-TM-500, Sept.  ’88.
  99. Molent, L., “Cold Proof Test of a Boron/Epoxy Reinforced F-111C Wing Pivot Fitting”, ARL-STR-TM-497, Aug.  ’88.
  100. Molent,  L.,  “Ambient  Proof  Test  of  a   Boron/Epoxy   Reinforced  F-111C Wing Pivot Fitting”, ARL-STR-TM-486, May ’88.
  101. Molent, L., Paul, J. and Jones, R., “Criteria for Matrix Dominated Failure”, ARL-STR-REP-432, Feb.  ’88.
  102. Molent, L., Callinan, R.J. and Jones, R., “Structural Aspects of the Design of an All Boron/Epoxy Reinforcement for the F-111 Wing Pivot Fitting – Final Report”, ARL-RES-REP-1, Nov. ’92.
  103. Molent, L. and Dunn, S., “A Test Methodology for an Investigation Into Heating and Cooling Phenomena in Grossly Deformed Tensile Metallic Bars”, ARL-STR-TM-482, Dec.  ’87.
  104. Molent, L. “RAAF Wall Traverse Trial: Woomera 1987 – Preliminary Wall Evaluation”, ARL-STR-TM-477, Dec.  ’87.
  105. Paul, J, and Molent, L., “Applications of Energy Density Theory in Cyclic Plasticity”, ARL-STR-TM-469, Aug.   ’87.
  106. Molent, L., and Ferrarotto, P., “Strain Survey of a Boron/Epoxy Reinforced F-111C Wing Pivot Fitting”, ARL-STR-REP-460, May ’87.
  107. Molent, L. and Jones, R., “Stress Analysis of a Boron/Epoxy Reinforcement for the F-111C Wing Pivot Fitting”,  ARL-STRUC-TM-456, March ’87.
  108. Molent, L., Ferrarotto, P. and Davis, M., “Thermal Strain Survey of an F-111C Wing Pivot Fitting”,  ARL-STR-REP-426, March ’87.
  109. Molent, L. and Sanderson, S., “Finite Element Derivation of the Stress Intensity Factors for an F-111 Wing Pivot Fitting Stiffener Crack”,  ARL-STR-TM-450,  Aug.  ’86.
  110. Molent, L., “Comparison of Theoretical and Test Results for the F-111 Wing Pivot Fitting Boron/Epoxy Doubler Specimen”,  ARL-STRUC-TM-465, Jan.  ’87.
  111. Jones, R., Callinan, R.J. and Molent, L., “Preliminary Design of a Boron/Epoxy Reinforcement for the F-111C Wing Pivot Fitting”,  ARL-­STR-REP-429, Aug. ’87.
  112. Molent, L., “Report on a Period of Attachment to the Department of Aviation, Canberra, June-September 1985”,  ARL-STR-TM-432, Jan.  ’86.
  113. Anderson, I. and Molent, L., “Resonance and Programmed Load Fatigue Test on the Empennage of a CT4 Aircraft”.   ARL-STR-TM-420 Oct.  ’85.
  114. Anderson, I.  and  Molent,  L., “Strain  Survey  of  a  CT4  Aircraft Tailplane, Elevator and Control Stick”,  ARL-STR-TM-422, Nov.  ’85.
  115. Anderson, I. and Molent, L., “Resonance Fatigue  Test  of the Empennage of a CT4 Aircraft”,  ARL-STR-TM-412, June ’85.