It's rare for an engine, propeller or airframe to fail catastrophically in flight. But when one does, more often than not, the culprit is metal fatigue. To make intelligent maintenance decisions, every aircraft owner needs a basic understanding of how metal behaves ... and why it fails. AVweb's Mike Busch offers a primer on the subject.
December 29, 1999
fatigue isn't a subject that usually keeps me awake at night. For most of the 30-odd years
during which I've been an aircraft owner, I figured it was a subject of interest mainly to
metallurgists and aeronautical engineers and other Ph.D. types, not to mere mortal
aircraft owners like me.
Figure 1 Under dye penetrant, the fatigue crack in my
cylinder head became painfully obvious. (Click on any image in this article for a
However, my interest in the subject was rekindled recently by a rash of maintenance
problems I encountered with my 1979 T310R. The problems started showing up during my
annual inspection last March. I did a compression check on my two 1000-hours-SMOH engines,
came up with mid-to-high 70s on all twelve cylinders, and figured my jugs were doing just
fine. But within an hour of starting the inspection, Phil Kirkham my IA for this year's
ordeal called me over and pointed to a nearly imperceptible blue stain in the vicinity
of the upper spark plug boss on the #5 cylinder of the right engine.
"Looks like we might have a cracked head," Phil told me.
"Boy, your eyes are sure better than mine," I replied. "I can just
barely see what you're talking about."
Figure 2 When I removed the cabin step to
re-bush it during the annual, I discovered a nasty fatigue crack in the magnesium support
"One way to know for sure," Phil said, reaching for an aerosol can of dye
penetrant. Within a few minutes, there was no question that Phil was right. The head was
definitely cracked, and the cylinder was trash. This was something of a watershed event
for me, since the twelve cylinders on my engines were the original twelve that rolled out
of the Cessna Wallace Plant in 1979. They'd survived 20 years, 3,000 hours, and one major
overhaul. But now, one of them had let me down. Could the other eleven be far behind?
Given that the engines were only 400 hours from published TBO, I decided the
appropriate course of action was to find a decent serviceable cylinder that would get me
to major overhaul, at which time it was pretty clear that all twelve jugs would have to be
replaced with new ones. I phoned Ken Tunnell at Ly-Con
Aircraft Engines in Visalia, Calif., explained my situation, and he fixed me up with a
nice-looking reconditioned jug for about half the cost of a new one. Ken runs a great
I figured that the worst was over. But later in the annual, I discovered another
serious problem. I'd removed my 310's retractable cabin step from the airframe in order to
replace its worn pivot bushings. With the step removed, I got a good look at the big
magnesium step support casting, and didn't like what I saw one bit. The casting had a
serious fatigue crack that had grown to the point that the part was on the verge of
fracturing in two. This one didn't require dye penetrant it was painfully obvious, even
to my untrained eye. Cessna wanted $900 for a new one, but I managed to get mine
weld-repaired (which is tricky business with magnesium, as you might imagine).
It Ain't Over Yet
Figure 3 My right prop started throwing red-dyed oil from
the #2 blade retention area. The prop shop suspected a fatigue crack in the blade
After a month of wrench swinging that seemed like it would never end, I finally got the
airplane back together. Phil signed off the annual and returned the plane to service, and
I looked forward to 11 months of hassle-free flying. But it was not to be.
In late April, I was flying up to Bend, Ore., to visit the Lancair Columbia 300
factory and have a close look at the newly certificated 300-hp composite speedster. About
an hour into the three-hour flight, I noticed a thin reddish streak starting to develop on
the top of the right engine nacelle. Unless it was bug blood, red fluid in that location
could only come from one place: my red-dyed-oil-filled propeller hub. Sure enough, upon
landing at Bend, I verified that the red liquid was indeed coming from the right prop hub.
As I write this, the prop is at the prop shop being torn apart. The verdict isn't yet in,
but one theory is that the source of the leak may turn out to be a tiny fatigue crack in
the retention nut that secures the #2 blade to the hub.
While all this was happening, I was deeply immersed in the ongoing TCM CSB 99-3
crankshaft debacle. Early in 1999, TCM became aware of seven crankshaft fatigue failures
in factory reman 520- and 550-series engines. These failures were extraordinary for
several reasons: they all occurred in new Vacuum Arc Remelt (VAR) cranks with very low time, and they all
occurred in virtually identical locations in relatively low-stress areas of the
crankshaft. Forensic investigation revealed that the failures had been caused by a stress
riser created by a faulty tool used to press counterweight hangar bushings into the
crankshaft during manufacture. The result was a massive inspection program affecting the
entire 1998 production of new and reconditioned 470/520/550 crankshafts, and the scrapping
of nearly 15% of those crankshafts.
So, with my airplane AOG and propless, and my e-mailbox full of messages from
disgruntled TCM engine owners, I decided to do some reading on the subject of metal
fatigue. It turned out to be a pretty interesting subject.
One of the best write-ups on this subject to be found anywhere appears in John
Schwaner's "Sky Ranch Engineering Manual," available from Sacramento Sky Ranch Inc. ($19.95,
1-916-421-7672). Much of the following discussion is derived from material in Chapters 1
and 7 of this excellent book.
Stress and Strain
Figure 4 Typical relationship between stress (force)
and strain (deformation) in metal.
Consider what happens when you apply force to a piece of metal: It deforms. The force
you apply is called stress, and the amount of resultant deformation is called strain. The
relationship between stress and strain is what defines the structural properties of the
metal. (See Figure 4.)
The deformation of a metal part in response to stress may be either elastic or plastic.
Elastic deformation is temporary when the stress is removed, the metal returns to its
original shape. The flexing of an airliner wing or the spring steel main landing gear on a
single-engine Cessna are examples of elastic response to stress. The slope of the
stress/strain curve determines the elasticity (stiffness) of the metal.
When metal is stressed beyond its elastic limit or yield point, the result is permanent
(or plastic) deformation when the stress is removed, the metal does not return to its
original shape. The ability of metal to be bent, stamped, forged or extruded into a
desired shape as well as its ability to bend before it breaks are the result of its
plastic properties. On the other hand, once a metal part is placed in service, it's
obviously important that it not be subject to stress in excess of its yield point.
When you think about it, this combination of elastic and plastic properties is what
makes metal behave like ... well ... metal. Many other familiar materials whether
flexible like rubber or brittle like glass are almost entirely elastic at ordinary
temperatures, and become plastic only when heated. Other materials like clay or putty have
little or no elasticity, and deform permanently with the slightest force.
Tension and Compression
Figure 5 Bending loads on a spring steel landing gear
result in both tension and compression stresses.
When we think about applying stress to a metal part, we usually think in terms of
tension in other words, applying a load that tries to pull the metal apart. Cylinder
studs and crankcase through-bolts are examples of metal parts that are loaded in tension.
Aluminum alloys may have tensile strengths between 20,000 and 80,000 PSI, while
high-tensile-strength steel can withstand 200,000 to 400,000 PSI or more.
If a metal part is subject to tensile stress in excess of its elastic limit, it may
start to crack. Over time, the crack may grow to the point that the part fractures in two.
Tension isn't the only kind of stress, however. We may load a metal part in
compression. Sufficient compression stress may exceed the elastic limit and result in
permanent deformation of the part. However, metal normally doesn't have a well-defined
yield point in compression, so compression doesn't normally cause cracking or fracture.
(Extremely hard and brittle metals may shatter under excessive compression, however.)
In real life, metal parts are often subject to complex combinations of tension and
compression stresses. When a part such as a wing spar or spring steel landing gear leg is
subjected to bending loads, for example, certain areas are stressed in tension while other
areas are stressed in compression. (See Figure 5.) The same is true of parts subjected to
torsion or shear loads. In such cases, we tend to be more concerned with the areas of the
part subjected to tension, because those are the areas that are most likely to crack and
Figure 6 Stress is normally concentrated at the
surface of a loaded part. Stress concentrations also occur at geometric discontinuities
so-called "stress risers" such as corners, holes, notches, threads,
scratches, nicks, and pits.
When a metal part is placed under load, stress is almost never uniformly distributed
through the part. Instead, it concentrates in certain areas. Naturally, those areas of
stress concentration are where the part is most likely to crack or fracture.
When a part is subject to bending or torsion loads, almost all of the stress (tension
and compression) occurs at the surface of the part. That's why many airplane parts are
hollow rather than solid. A hollow tube is very nearly as strong as a solid rod of similar
size, but the hollow tube is much lighter in weight. . The principal disadvantage of a
hollow part is that, if stressed beyond its elastic limit, it tends to fail much more
suddenly and catastrophically than a solid part.
The same principle explains why I-beam and C-beam structures (commonly used for wing
spars) carry virtually all their load in the top and bottom "caps," and very
little in the "web" area that connects the two. It also explains why it's possible
to put "lightening holes" in parts without weakening them significantly
Stress is also concentrated at and magnified by any geometric discontinuities in
the part, such as corners, holes, notches, threads, scratches, nicks and pits. Such
discontinuities are commonly referred to as "stress risers" and are almost
invariably where fatigue cracks begin. (See Figure 6.)
Think about the last time you struggled to rip open a bag of potato chips or peanuts,
for example. The thin plastic or cellophane material of the bag is nearly impossible to
tear unless you're fortunate enough to locate the tiny "open here" nick or to
create such a nick yourself with a pocket knife or your teeth. The nick concentrates the
stress enormously, and makes the bag easy to open.
So it is with metal: A tiny and seemingly innocuous nick, scratch or pit may act as a
stress riser that concentrates the surface stress enough to cause the part to crack and
ultimately fracture. Simple surface roughness may be enough to weaken a part
significantly, which is why highly stressed parts are usually machined or polished to a
smooth finish. In time, corrosion pits may mar this smooth surface enough to permit
fatigue cracking to begin.
Figure 7 Typical S/N curves for ferrous and non-ferrous
metals. Note that non-ferrous metals like aluminum have no fatigue limit. No matter how
low the stress level, they will eventually suffer fatigue failure.
Take an ordinary paper clip, straighten, and then bend it back and forth repeatedly
until it breaks in two. What happened? You just demonstrated metal fatigue.
If you'd examined the bend point of the paper clip under a microscope as you bent it
back and forth, you'd have seen one or more microscopic fatigue cracks develop on the
outside radius of the bend the portion subject to tension stress. As you repeated the
bending cycle over and over, you'd see the crack grow with each cycle until the paper clip
Surprisingly, it is not necessary to stress a metal part beyond the yield point in
order to generate a fatigue failure. Fatigue cracks can develop even when stresses remain
well within the elastic limit of the metal, given enough cycles. The lower the stress
level, the more cycles it takes before a fatigue fracture will occur. This can be plotted
in the form of what engineers call an "S/N curve." (See Figure 7.)
A heavily loaded steel part can be expected to endure ten million cycles or so before
failing from metal fatigue. That might sound like a lot, but a connecting rod, crankshaft
throw or cylinder hold-down stud gets that many cycles in about 140 hours of flight time.
With steel, there is a stress level below which fatigue failures do not occur: the fatigue
limit. A part loaded below the fatigue limit may eventually develop fatigue cracks,
but they won't grow to the point of fracture. Therefore, a steel part (such as a
crankshaft) can theoretically remain in service forever, provided it doesn't corrode or
wear beyond service limits.
In sharp contrast, aluminum and other nonferrous metals have no fatigue limit. No
matter how low the stress level, eventually the metal will suffer a fatigue failure if it
is subjected to enough cycles. This means that aluminum parts are inherently life-limited.
For some parts, such as wing spars, the frequency of stress cycles may be so low that the
predicted life is ridiculously long. But for high-cycle parts, such as cylinder heads,
crankcase halves and propeller blades, the fatigue life is very significant, as my cracked
#5 cylinder head demonstrated.
Torque and Preload
Figure 8 Fasteners which undergo cyclic tension loads must
be torqued to establish a "preload" that exceeds the maximum operating load. If
this is done, the fastener will not "see" the cyclic loads and will not be
vulnerable to fatigue, nor will the fastened parts be vulnerable to fretting.
It is crucial for fasteners that undergo cyclic tension loads such as crankcase
bolts and cylinder hold-down studs be torqued properly to ensure that they don't
fatigue and fail. Here's why.
Consider the cylinder whose flange is attached to the crankcase by studs and nuts, as
illustrated in Figure 8. Each time the cylinder goes through its compression and power
strokes, the cylinder tries to pull away from the crankcase. At a peak cylinder pressure
of 1,000 PSI, each firing load on a 5.25-inch bore is over 20,000 pounds. Since there are
eight hold-down studs for each cylinder, each sees a peak load of around 2,500 pounds. At
cruise RPM, this happens 1,200 times a minute. Imagine that the cylinder hold-down nuts
were torqued to establish a "preload" of only 2,000 pounds. During each
combustion cycle, at the moment of peak stress, the stud would be subject to cyclic stress
of an additional 500 pounds, which might cause the stud to elongate slightly (in
accordance with the stress/strain curve). This is a bad thing for two reasons: The
cylinder base flange and crankcase mounting pad will be subject to fretting, and the
hold-down studs will experience stress cycles that could eventually result in fatigue
failure of the studs.
On the other hand, suppose the cylinder hold-down nuts were properly torqued to
establish a preload of 3,000 pounds. Now, even under peak stress conditions, the cylinder
base flange remains firmly in contact with the crankcase mounting pad. The hold-down studs
remain under a constant 3,000 pound stress, and are not subject to cyclic fatigue cycles.
Believe it or not, broken cylinder hold-down studs may be caused by something as
innocuous as paint! It is essential that no paint be applied to the
cylinder-to-crankcase mating surfaces, or to the cylinder mounting flange where the
hold-down nuts attach. If any paint is present when the hold-down nuts are torqued in
place, the paint film will eventually wear away, relieving some of the initial fastener
preload. If the preload decreases to less than the peak cyclic stress, then fatigue cycles
and fretting damage may occur.
Propeller spinners and spinner bulkheads are also places where inadequate preload is
often responsible for fatigue failures. These parts are subject to extreme vibration, and
require sufficient preload to overcome cyclic stress that can result in fatigue failure.
In most McCauley constant-speed prop installations, spinner preload is adjusted with
fiberglass shims inserted between the propeller dome and the forward spinner bulkhead.
When fatigue cracks occur at the spinner or aft bulkhead, it's almost always because there
are not enough shims installed to provide the necessary preload.
Another way to help protect parts from fatigue is to build them with built-in stress
that counteracts some of the externally applied stress that results from loading. Since
fatigue is always caused by tensile stress, generally at the surface of a part, fatigue
resistance can be increased by inducing internal compressive stress at the surface.
One way of accomplishing this is to compress the surface material of the part by
subjecting it to high-pressure rollers or shot peening. Rolling is commonly used to
increase the strength of propeller blades and to create high-strength threads, while shot
peening is used on high-stress engine parts such as connecting rods.
Another technique is called "nitriding," and used to caseharden crankshafts,
camshafts, cylinder barrels, gears, and other highly stressed steel parts. The parts are
baked in an oven in an atmosphere of ammonia gas. The heat releases atomic nitrogen from
the ammonia, and the nitrogen combines with the metal at the surface and to a depth of
.020 inch or so. Since the nitrogen atoms occupy normally vacuous space in the crystalline
structure of the steel, they produce compressive internal stress that increases strength,
hardness, and resistance to wear and fatigue.
A nitrided part such as a crankshaft is best thought of as being like an egg: a
relatively elastic core surrounded by a very thin, very hard, very brittle case. The outer
nitrided layer gives the crankshaft greatly improved wear-resistance. However, just like
an eggshell, the brittle "nitride case" can crack easily if subjected to
excessive pressure (which is exactly what caused the recent massive TCM CSB 99-3
Furthermore, while fatigue cracks normally occur at the surface of a metal part where
they can readily be detected, a nitrided or shot-peened part may develop subsurface
fatigue cracks that cannot be detected during visual or dye penetrant inspections. This is
why sophisticated non-destructive testing (NDT) techniques such as ultrasound and X-ray
must often be used to inspect these parts for fatigue.
What's It All Mean?
Our metal airframes, engines and propellers are made from an eclectic combination of
materials with widely varying characteristics. Steel parts like crankshafts and
accessory gears and tubular engine mounts should theoretically be able to remain in
service forever, provided they are loaded below their fatigue limits, and protected from
excessive wear, damage and corrosion. Aluminum parts, on the other hand, have no fatigue
limit. If they are subject to cyclical stress (as most are), they have a finite service
life and must be inspected regularly for fatigue cracking.
Cylinder heads are particularly vulnerable to fatigue failure, as I found out
firsthand. If you think about it, cylinder heads have just about everything going against
them, fatigue-wise. They're subject to an extraordinary amount of cyclic stress. They're
made of aluminum alloy so they're inherently life-limited. They operate at high
temperatures, which lowers the yield point of the metal and accelerates the effects of
fatigue. (The fatigue strength drops rapidly with increasing temperature, particularly as
CHTs rise above 400° F.) They're manufactured with rough
surfaces and machined with cooling fins and threaded areas and all sorts of holes, all of
which provide stress risers where fatigue cracks can originate. And, they're constantly
bathed with hot and highly corrosive exhaust gas which further weakens and pits the
surface of the head, particularly in the exhaust port area where many head cracks start.
Frankly, it's amazing that they last as long as they do.
An old rule of thumb states that once a cylinder has made it through two TBOs, the
likelihood of fatigue cracking increases significantly. The published TBO for my
TSIO-520-BB engines is 1,400 hours, which puts my 3,000-hour jugs a bit beyond twice TBO.
So you could say that my cracked #5 cylinder head occurred right on schedule, so to speak.
The question is: Was this a fluke, or are the other 11 cylinders going to follow suit
It's not worth trying to get heroic with weld repairs to a cylinder heads of the
vintage that mine are. Best to accept the fact that they're long in the tooth and bound to
give up the ghost sooner or later probably sooner. Between now and major overhaul time,
I'll have to watch my jugs like a hawk for the tell-tale signs of fatigue cracking
mainly subtle fuel and oil stains where there shouldn't be any, and cooling fins that go
"plunk" instead of "ping!" With luck, I'll nurse em along
til overhaul time, at which point they will wind up as scrap metal to come back as
somebody's Coca-Cola can.
What about my cabin step support casting that nearly fractured from fatigue? There are
some lessons learned there, too. Although this part is buried under the floorboards and
very difficult to inspect, it is subject to extreme cyclical stress every time someone
enters or leaves the cabin. The casting is made of magnesium, a material that is more
granular and brittle and prone to rapid cracking than aluminum. The crack originated at a
sharp corner of the casting that was not properly radiused during manufacture to minimize
the stress concentration at that point ... but it is now, after I spent an hour filing and
polishing it before reinstallation!
Most importantly, this casting was out of sight and out of mind. It wasn't on any
Cessna 310 annual inspection checklist, and none of the experienced twin Cessna mechanics
I talked to remember ever making a practice of trying to inspect it. That's going to
change, at least on my airplane.
As for my propeller hub that started throwing red-dyed oil, the problem turned out not
to be fatigue-related after all. Instead, it turned out to be caused by loss of torque on
the #2 blade retention nut, caused by can you guess? the presence of paint on
the threaded area of the hub when the prop was assembled during the previous overhaul.
Turns out that the prop shop had hired a new fellow in its paint shop, and apparently he
didn't realize that it was a no-no to paint the hub threads. The paint film gradually wore
down, causing a loss of preload, and could have developed into a life-threatening
situation if not detected early. The problem didn't show up until three years after the
overhaul, in the form of a tiny leak of the red-dyed oil that's there specifically to make
hub cracks detectable. Much to its credit, the prop shop re-overhauled both of my props at