What Is Metal Fatigue? Why Metal Breaks After Repeated Stress
Metal fatigue is progressive, localized damage caused by repeated or fluctuating stress or strain. A small crack can start at a notch, weld toe, thread, scratch, pore or corrosion pit; grow a little with many load cycles; and finally leave too little sound material to carry the next load. That is why a part may fracture even when its nominal service stress stayed below the metal’s static yield strength.
The short engineering answer
Fatigue is not simply a metal “getting weak everywhere.” It is a local crack process controlled by the complete combination of load history, geometry, surface, manufacturing condition, environment and inspection capability.
Repeated variation usually matters more than one static load value.
Notches, welds, threads, pits, pores and scratches amplify local cyclic demand.
The final fast fracture may be only the last fraction of the component’s damage history.
Design, process, assembly, duty cycle, environment and inspection must agree.
How does repeated stress break metal?
A fatigue crack normally develops through three practical stages. The boundaries are not perfectly sharp, and a pre-existing flaw can shorten or almost eliminate the initiation stage.
Microscopic cyclic plastic strain accumulates at a vulnerable surface, microstructural feature or defect. A tiny crack forms even though the entire part may still look elastic and unchanged.
Each damaging cycle advances the crack by a small amount. Growth rate depends on crack size, stress range, stress ratio, load sequence, environment, residual stress and geometry.
When the remaining ligament can no longer carry the load—or the crack reaches a critical condition—the part separates rapidly. This final event is often overload of the reduced section.
Calling a failure “fatigue” identifies the mechanism, not the root cause. The root cause is why the damaging cyclic load and the vulnerable location existed: poor radius, vibration, misalignment, weld detail, surface damage, corrosion, process variation, overload sequence, inadequate inspection—or a combination.
Why can fatigue happen below yield strength?
Yield strength comes from a monotonic material test and describes bulk behavior under a defined loading condition. A component is not a smooth coupon. A sharp radius, keyway, thread root, weld toe, pore, inclusion, scratch or corrosion pit can create much higher local stress and microscopic cyclic plastic strain than the nominal drawing stress suggests.
Repeated local slip can produce irreversible microstructural change at the hot spot. The entire part does not have to yield visibly for a fatigue crack to begin. This is why “the stress was below yield” is not a valid fatigue clearance by itself.
Does every repeated load cause fatigue?
No universal statement is safe. Whether damage accumulates depends on the metal and condition, stress or strain range, mean stress, number and sequence of cycles, temperature, corrosion, geometry, surface, residual stress and failure criterion. Some material systems and environments show practical endurance behavior; others continue to show declining strength at very high cycle counts.
A realistic assessment therefore defines the complete duty cycle and the actual production condition instead of relying on a single static strength value.
Maximum stress alone is not enough
A fatigue calculation needs the alternating part of the load, the mean level and the number of repetitions. Fully reversed loading, tension–tension loading, start-stop torque, pressure pulsation, thermal cycling and random vibration can have very different crack-driving effects even if one maximum value matches.
The stress ratio R = σmin/σmax helps describe the cycle. For many unwelded materials, a more tensile mean stress can reduce fatigue resistance. Welded structures are often assessed with detail-category methods that already account for high tensile residual stress, so the governing design rule must be followed rather than mixing methods.
σmaxMaximum stressThe highest stress in one defined cycle.
σminMinimum stressThe lowest stress in the same cycle.
ΔσStress rangeσmax − σmin; widely used in fatigue assessment.
σaStress amplitudeHalf the stress range for a regular cycle.
σmMean stressAverage of maximum and minimum stress.
RStress ratioσmin/σmax, reported with test data.
NfFatigue lifeCycles to a defined failure or crack criterion.
RunoutTest stopped unfailedCensored data—not proof of infinite life.
What can a fatigue fracture surface reveal?
A fatigue surface may show one or more origins, a smoother progressive-growth region, curved progression or beach marks, ratchet marks from multiple origins and a rougher final-fracture area. Microscopic striations may be present in some alloys and growth conditions.
These features are useful, but none is guaranteed. Beach marks can reflect changes in loading or environment rather than every cycle. One microscopic striation should not automatically be equated with one service cycle. Corrosion, rubbing after fracture, oxidation, handling or cleaning can obscure the evidence.
Quarantine the assembly, photograph it in place, preserve orientation and mating parts, protect fracture faces and keep records of load, vibration, temperature, alarms and recent maintenance. Do not wire-brush, sandblast, polish, force mating faces together or remove corrosion products before a failure analyst reviews the evidence.
How to read an S–N curve
An S–N or Wöhler curve relates a defined cyclic stress measure, S, to the number of cycles, N, associated with a defined failure criterion. Test laboratories run multiple specimens at several stress levels because fatigue results scatter—even among nominally identical specimens.
The curve is meaningful only with its conditions: alloy and heat, product form, orientation, heat treatment, hardness, surface finish, specimen geometry, notch, stress ratio, waveform, frequency, temperature, environment, failure criterion, runout policy and statistical basis.
Do not transfer a polished-coupon curve directly to a welded, corroded or differently sized component without a valid method. Do not extrapolate beyond the tested range. Do not interpret a runout as infinite life.
Local cyclic plasticity matters
Strain-life methods are often preferred when severe mechanical or thermal cycling creates meaningful plastic strain. “Below 105 cycles” is a useful approximate context in some standards—not a universal boundary.
Nominal response is mostly elastic
Stress-life methods are common when cyclic strains are predominantly elastic. Geometry, mean stress, surface, defects and environment still control how coupon data transfer to a part.
Internal origins can become important
At very large cycle counts, subsurface inclusions, pores and microstructure may govern some materials. The start of “VHCF” is application- and literature-dependent, not a fixed universal number.
Ten factors that control fatigue life
No single “fatigue strength” follows a metal everywhere. The component’s life emerges from the complete system below.
Stress or strain range
Larger cyclic ranges generally increase damage and accelerate crack growth. Local hot-spot range matters more than a remote nominal value.
Mean and maximum level
Tensile mean stress can reduce resistance in many unwelded applications; maximum stress also affects crack-tip conditions and overload interactions.
Geometry and load path
Small radii, holes, threads, keyways, abrupt thickness changes, poor stiffness transitions and eccentric loading concentrate cyclic demand.
Surface condition
Machining marks, grinding burns, scratches, dents, burrs, coating damage, roughness and unfavorable lay can create initiation sites.
Material and microstructure
Grade, heat, cleanliness, inclusion population, grain structure, hardness, heat treatment, texture and orientation all influence response.
Defects and discontinuities
Porosity, shrinkage, lack of fusion, laps, seams, decarburization and additive-manufacturing flaws can shorten initiation life or behave like initial cracks.
Residual stress
Welding, machining, forming, heat treatment, coating and peening can leave tensile or compressive stress that changes local fatigue behavior.
Size and stress gradient
Large components sample more material and may have different constraint, defect populations and gradients than small laboratory specimens.
Environment and temperature
Corrosion, humidity, salt, chemicals, hydrogen, lubrication, vacuum, temperature and dwell can change initiation and growth rates.
Load sequence and assembly
Overloads, resonance, start-stop events, preload, alignment, fit, contact, fretting and maintenance changes can alter the damage history.
Why a stronger metal does not always make a stronger detail
In a rotating shaft, the keyway, shoulder radius, oil hole, press fit, fretting zone or machining mark may govern long before the base metal’s tensile strength is reached. Alignment and balance determine the alternating bending load, so replacing a shaft with a higher-strength grade without correcting the load path can leave the same fatigue origin.
In an as-welded structure, toe and root geometry, attachment detail, undercut, misalignment, incomplete fusion, residual tensile stress, thickness and environment frequently dominate fatigue behavior. Many design systems therefore classify the weld detail and apply detail-category S–N curves, rather than crediting base-metal tensile strength directly.
Grinding, stop-drilling, peening, weld repair or reinforcement can be appropriate only after the full crack extent, critical location, residual stress, load path, material condition and root cause are evaluated. Surface improvement does not erase an existing crack below the treated surface.
Metal fatigue versus other failure modes
A component can show more than one mechanism. Fatigue growth may end in final overload; corrosion may accelerate fatigue; elevated temperature may introduce creep-fatigue interaction.
| Failure mode | Primary driver | Typical clues | Key distinction |
|---|---|---|---|
| Fatigue | Repeated or fluctuating stress/strain | Origin at a hot spot, progressive region, possible progression marks, final fast-fracture area | Can develop below nominal static yield; damage is cycle- and condition-dependent |
| Static overload | One load exceeds immediate strength or stability | Gross plastic deformation, ductile tearing, buckling or rapid brittle fracture | No long progressive cyclic-growth history is required |
| Brittle fracture | Crack, constraint, low toughness, temperature and high driving force | Rapid cleavage-like fracture with limited gross deformation in susceptible conditions | Can be the final event after fatigue reaches critical size |
| Creep / creep-fatigue | Time at temperature plus stress, with or without cycling | Time-dependent deformation, grain-boundary damage, dwell sensitivity | Time and temperature become central, not just cycle count |
| Stress-corrosion cracking | Susceptible material + tensile stress + specific environment | Environment-specific branching or intergranular/transgranular cracking | May occur under sustained stress; corrosion fatigue requires cycling |
| Wear / contact fatigue | Repeated rolling or sliding contact, traction and lubrication condition | Pitting, spalling, micropitting or subsurface-origin damage | Contact stress field and tribology govern the damage site |
Which assessment route should your part start with?
Choose the closest project conditions. This tool does not calculate fatigue life; it identifies the level of engineering evidence likely needed before a sourcing, design or inspection decision.
Describe the component
Use actual service and production conditions where possible.
Start with a detail-based fatigue assessment
Variable loading, a welded hot spot and meaningful failure consequence require more than a material datasheet or smooth-coupon S–N curve.
Planning aid only. It does not replace a code-based fatigue calculation, fracture-mechanics assessment, qualified inspection or competent engineering approval.
How engineers estimate fatigue life—and where each method stops
Method selection depends on whether the problem is mostly elastic, locally plastic, already cracked or too complex for coupon transfer.
Mostly elastic cycling
Uses stress range or amplitude versus cycles for a defined material or detail. Appropriate corrections and a valid statistical/design basis are needed for mean stress, size, surface, notch, environment and reliability.
Local cyclic plasticity
Tracks total, elastic and plastic strain where notches, start-stop events or thermal cycling produce plastic response. Local multiaxial strain and cyclic material behavior must be represented.
Known or assumed crack
Integrates crack-growth data with geometry, initial flaw, load history and critical size. Small cracks, closure, residual stress, overloads and environment can invalidate simple long-crack assumptions.
System-level validation
Tests representative geometry, joints, assembly and spectrum. It can capture interactions that coupons miss, but the sample size, runout, failure criterion and production representativeness still matter.
Paris-type crack-growth relation
This is a useful mid-growth, linear-elastic correlation—not a law for the complete crack-growth curve. It should not be used blindly near threshold, for micro/small cracks, near rapid instability, under large-scale yielding or when the test and service conditions do not satisfy transferability assumptions.
Variable-amplitude damage
Palmgren–Miner linear damage is widely used as an approximation after a service history is cycle-counted, often by rainflow. Failure is frequently represented near D = 1, but real failure sums vary. Sequence, overloads, mean stress, crack closure, corrosion and residual-stress evolution are not fully captured by the linear rule.
Record maximum and minimum loads, sequence, dwell, frequency, starts, stops, impacts, pressure, torque, acceleration, vibration, thermal gradients and unusual events. A spreadsheet built from one “typical load” can be more precise-looking and less accurate than a bounded test based on measured service data.
How can metal fatigue be prevented?
The best time to manage fatigue is before the first production lot. The most effective solutions reduce the crack-driving stress and remove vulnerable hot spots rather than relying on inspection alone.
Define the real duty cycle
Capture load ranges, mean levels, sequence, frequency, starts, stops, thermal events, vibration, resonance, assembly boundary conditions and environmental exposure. Define required life and failure criterion.
Reduce cyclic demand
Change stiffness, load path, support, balance, speed, preload, damping or control logic to reduce the damaging stress/strain range and avoid resonant amplification.
Improve the hot-spot geometry
Use generous transitions, smooth load introduction, controlled holes and threads, adequate edge distance and reduced eccentricity. Evaluate where stiffness changes, not just where material is thin.
Control material and process
Specify grade, heat treatment, product form, cleanliness, orientation, hardness, defect limits, weld detail, special processes and production changes that affect fatigue-critical condition.
Protect surface and environment
Control roughness, lay, burrs, dents, grinding burns and coating damage. Use qualified corrosion protection, lubrication and surface-treatment processes appropriate to the actual material and load.
Validate and monitor
Combine representative testing, analysis, traceability, first-article checks, process capability and a qualified inspection plan tied to detectable and critical flaw sizes.
How are fatigue cracks detected?
Inspection method depends on material, crack orientation and location, geometry, coatings, access, surface condition and the flaw size that must be found. A negative inspection result means no reportable indication was detected within the qualified capability, coverage and acceptance criteria of that procedure. It does not prove that the part is crack-free.
Inspection intervals should be connected to a damage-tolerance or code basis: the method’s reliably detectable size, expected crack-growth behavior under the real spectrum and environment, critical crack size, access and safety factor—not a generic calendar interval.
| Method | Best suited to | Important limitation | Fatigue-program use |
|---|---|---|---|
| Visual / enhanced visual | Accessible surface cracks, distortion, corrosion, fretting and leak evidence | Small, tight, coated, hidden or subsurface cracks may be missed | Frequent screening, documentation and targeting of further NDT |
| Liquid penetrant | Surface-breaking discontinuities in nonporous materials | Needs clean surface access; cannot detect a fully subsurface crack | Machined parts, nonferromagnetic alloys and exposed weld surfaces |
| Magnetic particle | Surface and near-surface discontinuities in ferromagnetic materials | Not for aluminum, copper or most austenitic stainless; orientation and magnetization matter | Steel shafts, gears, fasteners and weld details |
| Eddy current | Surface/near-surface cracking in conductive materials, sometimes through thin coatings | Probe, geometry, conductivity, lift-off, crack orientation and calibration affect response | Aircraft holes, fastener regions, tubes and localized scanning |
| Ultrasonic / phased array | Internal and surface-connected flaws with suitable sound paths | Needs access, coupling, qualified calibration and skilled interpretation; sizing uncertainty remains | Thick sections, welds, shafts and encoded monitoring |
| Radiography / CT | Volumetric discontinuities and complex internal geometry | Planar crack detectability depends strongly on orientation; safety, access and cost matter | Castings, AM parts and selected high-value assemblies |
| Acoustic emission / monitoring | Detecting active events or changes during load | Noise, source location and interpretation require qualification; another method may be needed to size | Large structures, proof tests and condition monitoring |
Where fatigue risk hides in real production
These examples show why the corrective action is rarely just “buy stronger metal.”
Check balance, bearings, alignment, fillet radius, keyway finish and actual bending spectrum before changing alloy or hardness.
Measure vibration and operating modes, review detail category and stress range, then control toe geometry, stiffness transition and weld quality.
Model startup/shutdown gradients, supports, nozzle loads and dwell. Inspect the real hot spot and consider creep-fatigue or corrosion interaction where relevant.
Control build orientation, process qualification, heat treatment/HIP, machining, NDT capability and representative fatigue data for the production route.
Specify hole preparation, edge condition, fit, preload method, lubrication, locking, inspection and repair limits. A stronger bolt does not repair a damaged load-transfer joint.
After a break, preserve the story in the evidence
A useful investigation separates the fracture mechanism from the systemic cause. It combines scene documentation, fractography, material verification, manufacturing history, load reconstruction and hypothesis testing.
- Make safe and quarantine: identify every affected serial, lot, sister component and mating part.
- Document before disturbance: orientation, fragments, alarms, operating state, corrosion, wear, fastener condition and maintenance changes.
- Preserve fracture surfaces: protect from contact, moisture, cleaning and coating removal.
- Collect the real history: load, strain, vibration, temperature, pressure, speed, starts, stops, impacts and abnormal events.
- Examine at multiple scales: visual and NDT, macrofractography, microscopy, chemistry, hardness, microstructure and dimensional checks.
- Reconstruct stress and process: geometry, assembly, residual stress, defects, surface, environment and changes.
- Test the competing hypotheses: reproduce the hot spot or failure mode with analysis, measurement and representative testing.
- Verify corrective action: remove the cause, not only the visible crack; update drawing, process, inspection and change control.
What should a fatigue-critical RFQ specify?
“Make it from Grade X” is not a fatigue requirement. Give the supplier enough information to control the real crack drivers and prove the quoted process represents production.
Complete duty cycle: maxima, minima, ranges, mean, sequence, cycles, frequency, dwell, overloads and abnormal events.
Boundary conditions: supports, preload, alignment, fits, assembly sequence, contact and resonance-avoidance requirements.
Environment: temperature, humidity, salt, chemicals, corrosion, hydrogen, lubrication, vacuum and cleaning exposure.
Material condition: exact specification, heat treatment, hardness, product form, orientation, cleanliness and traceability.
Defect limits: cracks, pores, inclusions, seams, laps, lack of fusion, decarburization and surface anomalies.
Critical geometry: radii, transitions, holes, threads, keyways, wall thickness, tolerances, alignment, runout and balance.
Surface requirements: roughness, lay, burr, scratch, gouge, recast, grinding-burn, coating and handling limits.
Weld and joint controls: detail, procedure, heat input, toe/root profile, penetration, undercut, misalignment and repair limits.
Validation basis: S–N, strain-life, crack-growth or full-scale method, sample size, runout, failure criterion and statistics.
NDT capability: method, procedure, coverage, calibration, sensitivity/POD basis, acceptance criteria and personnel qualification.
Production evidence: first article, special-process records, capability data, retained samples, audits and periodic revalidation.
Change control: written approval before changes to mill, process, machine, toolpath, heat treatment, weld, coating, NDT or repair.
Which fatigue standard answers which question?
This snapshot was reviewed on July 31, 2026. Always confirm the active licensed edition, governing design code and laboratory scope before placing an order.
| Standard | Primary purpose | Procurement note |
|---|---|---|
| ASTM E466-21 | Force-controlled, constant-amplitude axial fatigue of metallic specimens in a predominantly elastic regime | Specimen test—not an automatic full-component life guarantee |
| ASTM E606/E606M-21 | Strain-controlled fatigue and cyclic stress–strain behavior | Useful when local plastic strain or thermomechanical cycling matters |
| ASTM E647-24 | Fatigue crack-growth rates from near-threshold toward instability | Residual stress, R, small cracks, environment and closure affect transferability |
| ASTM E1049-85(2023) | Cycle-counting methods, including rainflow, for irregular histories | It describes methods; it does not guarantee which model fits a given service history |
| ASTM E2368-25 | Strain-controlled thermomechanical fatigue testing | Define temperature–strain phase, waveform, environment and specimen condition |
| ISO 1099:2017 | Axial force-controlled constant-amplitude metallic-specimen fatigue | Published edition; a replacement edition is progressing—verify current status |
| ISO 12106:2017 | Axial strain-controlled fatigue testing | Published edition with revision underway—verify current status |
| ISO 12107:2012 | Statistical planning and analysis of fatigue data | Use to define sample size, confidence, runout and reporting strategy |
| ISO 12108:2018 | Fatigue crack-growth testing | Predominantly linear-elastic Mode I scope; verify revision status and suitability |
| ISO 12110-1/-2:2013 | Variable-amplitude testing principles and cycle counting | Confirmed in 2024; scope exclusions still need review for the project |
| ISO 1143:2021 | Rotating-bar bending fatigue testing | Useful for defined metallic specimens, not direct proof for every shaft detail |
A purchase order should still define material condition, specimen or component geometry, stress/strain measure, R ratio, waveform, frequency, environment, failure criterion, runout, sample selection, statistical basis, reporting and how the results will be used.
Metal-fatigue myths that create expensive failures
Local cyclic plasticity at a notch, weld, scratch, pit or defect can accumulate while nominal stress remains below static yield.
Fatigue resistance depends on condition, life, mean stress, surface, size, geometry, statistics and environment.
As-welded detail category, geometry, residual stress, defects and stress range often govern more than base-metal strength.
A runout is a test stopped without reaching the failure criterion. It is censored evidence at those conditions.
The linear rule is an approximation and does not fully capture sequence, overload, corrosion, residual stress or scatter.
Every method has a detection capability, coverage, orientation sensitivity and probability of detection.
Macroscopic progression marks can reflect changes in loading or environment; they are not a universal cycle counter.
It may reduce crack-tip demand in selected cases, but only after crack extent, load path, critical size and root cause are assessed.
Metal fatigue FAQ
What is metal fatigue in simple terms?
Metal fatigue is progressive localized damage caused by repeated or fluctuating stress or strain. A small crack starts at a vulnerable point, grows with additional cycles and eventually leaves too little sound material to support the load.
Can metal fatigue happen below yield strength?
Yes. A notch, weld toe, thread, scratch, pit, inclusion or crack tip can create much higher local cyclic stress and microscopic plastic strain than the nominal component stress. The whole part does not need to yield visibly.
What are the three practical stages of fatigue failure?
Crack initiation or small-crack development, stable cycle-by-cycle macrocrack propagation and final rapid fracture. A pre-existing defect can greatly shorten the initiation stage.
How many cycles cause metal fatigue?
There is no universal number. Severe cyclic plastic strain can fail a part in relatively few cycles, while mostly elastic cycling may require millions or more. Geometry, surface, defects, environment, mean stress and sequence change the answer.
What is the difference between S–N and strain-life analysis?
S–N methods relate cyclic stress to life and are common when response is predominantly elastic. Strain-life methods include elastic and plastic strain and are useful when local cyclic plasticity, start-stop or thermal cycling matters.
Is 10⁵ cycles the exact boundary between low- and high-cycle fatigue?
No. Some standards use approximately 10⁵ cycles as contextual guidance for strain-controlled applications, but the transition depends on material, local strain, geometry, temperature and the analysis framework.
When is Paris law valid?
A Paris-type relation is mainly a mid-growth, linear-elastic correlation for appropriate long-crack conditions. It is not universally valid near threshold, for micro/small cracks, near instability, under large-scale yielding or after complex load-sequence effects without qualification.
Does Miner’s rule predict exact remaining life?
No. It is a linear cumulative-damage approximation based on counted cycles and S–N data. Real damage can depend on sequence, overloads, mean stress, corrosion, residual stress, crack closure and scatter.
Why are welded joints often fatigue-critical?
Weld toe/root geometry, attachment details, undercut, misalignment, lack of fusion, thickness and high tensile residual stress create strong local crack drivers. Detail-category fatigue data often govern more than base-metal tensile strength.
Can NDT certify that a part is crack-free?
No. A qualified inspection can state that no reportable indication was detected within the capability, coverage and acceptance criteria of the method and procedure. Detection remains probabilistic and geometry-dependent.
Can a fatigue crack be repaired?
Sometimes, after engineering evaluation. The repair must address the full crack, critical size, load path, residual stress, material, inspectability and root cause. Replacement may be safer or more economical for critical components.
What information should I send for a fatigue review?
Provide the drawing, material and condition, manufacturing route, complete load/temperature/environment spectrum, required life, failure consequence, surface and defect limits, inspection plan, assembly/preload, production volume and any failed-part evidence.
Authoritative sources used for this guide
These sources define testing scope, transferability limits, crack growth, welded-detail behavior and inspection boundaries. Standards may be revised; verify the current licensed edition for contractual use.
- ASTM E466-21 — force-controlled constant-amplitude axial fatigue testing of metallic specimens.
- ASTM E606/E606M-21 — strain-controlled fatigue testing and cyclic material response.
- ASTM E647-24 — fatigue crack-growth rates and important limitations involving small cracks, closure, residual stress and environment.
- ASTM E1049-85(2023) — cycle-counting methods for fatigue analysis.
- ISO 1099:2017 and ISO 12106:2017 — axial force- and strain-controlled fatigue testing.
- ISO 12107:2012 and ISO 12108:2018 — statistical fatigue planning and fatigue crack-growth testing.
- NASA, Fatigue Testing — cyclic plasticity, stress-life/strain-life concepts and specimen testing.
- NIST, Failure Analysis of the WWVB Tower — a practical fatigue investigation involving design detail, radius, material and heat-treatment specification.
- NIST, Additive Manufacturing Fatigue and Fracture — AM defects, fatigue performance, NDE and qualification challenges.
- FHWA, Design and Evaluation of Steel Bridges for Fatigue and Fracture — stress concentrations, weld details, crack growth, design and inspection.
- FHWA, NDE technologies for fatigue cracks — capabilities and limitations of advanced inspection methods.
- TWI, Fatigue design rules for welded structures — detail-category S–N curves, residual stress, size, environment and cumulative damage.
Related material and welding guides
Fatigue decisions improve when material behavior, manufacturing route, weld geometry and thermal history are considered together. These guides provide the next layer of context.
Review the load, hot spot and production condition together.
Send Oceanplayer your drawing, material condition, manufacturing route, service spectrum, environment, required life, inspection basis and failure consequence. We can help organize the information needed for a manufacturability discussion, sample validation or supplier review.