The Effect of Tropical Environment on Fatigue Failure in Royal Malaysian Airforce (RMAF) Aircraft Structure and Operational Readiness

Venugopal, Arvinthan; Mohammad, Roslina; Koslan, Fuad Shah; Bakar, Syed Roslee Sayd; Ali, Alizarin

doi:10.3390/ma14092414

Cited by 5 publications

(3 citation statements)

References 13 publications

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“…Despite the effective use of chromate-containing coatings on aluminium aircraft parts, corrosion and fatigue remain the primary contributors to structural failure in aircraft [9][10][11]. Corrosion manifest in various forms observed during aircraft operation, including galvanic corrosion, exfoliation corrosion, pitting corrosion, crevice corrosion, etc.…”

Section: Introductionmentioning

confidence: 99%

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Mol,

Homborg,

't Hoen-Velterop

et al. 2024

Preprint

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Section: Introductionmentioning

confidence: 99%

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Mol,

Homborg,

't Hoen-Velterop

et al. 2024

Preprint

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“…One of the leading causes of fatigue failure in the RMAF is its surrounding tropical environment, besides the operational mission, and this leads to structural corrosion and corrosion-induced cracking [ 5 ]. Fatigue management in RMAF aircraft was only via documentation of flight hours and landing cycle throughout the fleet, as stipulated by the original equipment manufacturer (OEM).…”

Section: Introductionmentioning

confidence: 99%

Structure Life Extension towards the Structural Integrity of Sukhoi Su-30MKM

Venugopal¹,

Mohammad²,

Koslan³

et al. 2021

Materials

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The airframe structures of most fighter aircraft in the Royal Malaysian Airforce have been in service for 10 to 20 years. The effect of fatigue loading, operating conditions, and environmental degradation has led to the structural integrity of the airframe being assessed for its airworthiness. Various NDT methods were used to determine the current condition of the aircraft structure after operation of beyond 10 years, and their outcomes are summarized. In addition, although there are six critical locations, the wing root was chosen since it has the highest possibility of fatigue failure. It was further analyzed using simulation analysis for fatigue life. This contributes to the development of the maintenance task card and ultimately assists in extending the service life of the fighter aircraft. Using the concept of either safe life or damage tolerance as its fatigue design philosophy, the RMAF has adopted the Aircraft Structural Integrity Program (ASIP) to monitor the structural integrity of its fighter aircraft. With the current budget constraints and structural life extension requirements, the RMAF has embarked on the non-destructive testing method and engineering analysis. The research outcome will enhance the ASIP for other aircraft platforms in the RMAF fleet for its structure life assessment or service life extension program.

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“…Royal Malaysian Air Force (RMAF) is no exception to this. Since the Aircraft Life Extension Program by the Original Equipment Manufacturer (OEM) usually costs relatively much, RMAF has embarked on several life extension projects [3].…”

Section: Introductionmentioning

confidence: 99%

Crack Growth Prediction on Critical Component for Structure Life Extension of Royal Malaysian Air Force (RMAF) Sukhoi Su-30MKM

Venugopal¹,

Mohammad²,

Koslan³

et al. 2021

Metals

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The critical aircraft structure, being the load-bearing members, is a vital component for any aircraft. The effect of fatigue loading, operating conditions, and environmental degradation has caused the structural integrity of the airframe to be assessed for its airworthiness requirement. Using the fatigue design concept of Safe Life, the RMAF adopts the Aircraft Structure Integrity Program (ASIP) to monitor the structural integrity of its critical components. RMAF has produced the task card using the engineering analysis concept on the aircraft’s critical structure. Various Computer-Aided Engineering (CAE) methods were used, and for this analysis, the Crack Growth Prediction method was used to determine the crack growth behavior and its ultimate failure point in case of any crack occurrences. Although there are six critical locations, the wing root is chosen since it has the highest possibility of fatigue failure. The analytical methods which were discussed are Crack Growth Analysis and Low Cycle Fatigue. For the numerical method, NX Nastran was used for the simulation of crack growth. The result from the crack growth analysis was validated with the numerical result. The conclusion is that, based on the fatigue life cycle, the wing root structure condition is not affected by severe damage, and its failure is approximately around 30 to 100 years for both the through hole and through side crack. Thus, its structural life can be extended. The research outcome will be on the extension of the structure life of the aircraft wing.

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The Effect of Tropical Environment on Fatigue Failure in Royal Malaysian Airforce (RMAF) Aircraft Structure and Operational Readiness

Cited by 5 publications

References 13 publications

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Unravelling Corrosion Degradation of Aged Aircraft Components Protected by Chromate-Based Coatings

Structure Life Extension towards the Structural Integrity of Sukhoi Su-30MKM

Crack Growth Prediction on Critical Component for Structure Life Extension of Royal Malaysian Air Force (RMAF) Sukhoi Su-30MKM

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