1 glossary

Table of Contents

Aircraft Structures Design and Analysis G-1 University of Kansas, July 2007

Glossary of Terms....................................................................................................................................3

Definitions...............................................................................................................................................12

Symbols ...................................................................................................................................................14

Acronyms................................................................................................................................................16

University of Kansas, July 2007 G-2 Aircraft Structures Design and Analysis

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Glossary of Terms


AILERON. Hinged sections of the trailing edge of the left and right wings that operate together to provide lateral control. When one aileron is raised, the opposite is lowered, producing rolling movements around the longitudinal axis of the aircraft.

Aileron

AIR BRAKE: A device to increase the air resistance of an airplane, thus slowing its speed (see SPOILER).

AIRFOIL. A surface, such as an airplane wing, aileron, or rudder, designed to obtain a reaction fromt eh air through which it moves.

ANGLE OF ATTACK. The angle at which the air meets the wing. The usual maximum angle of attack short of the stall is 14 to 17 degrees. The angle between the line of the normal wind direction and the chord and an airfoil.

ASPECT RATIO. The relation of wingspan to wing surface area, ascertained by dividing span dimension (squared) by the wing surface area.

High-Aspect-Ratio WingLow-Aspect-Ratio Wing

BONDING. A process similar to gluing, used to attached stringers to fuselage skins and also to attach doubler-skins anywhere an increase in skin thickness is required to reduce stresses.

BOOM (flying boom). The extendable refueling tube designed and developed at Boeing for the KC-97 and KC-135 tanker planes. Boom position is controlled by aerodynamic control surfaces, arranged in a V-configuration, called ruddervators.

Ruddervators

Boom tube

BOX TORQUE (landing gear). A tapered box-like structure attached to the aft side of the rear spar to support the landing gear on the KC-135 and 707-series aircraft.

Torque Box

BOX TORSION (stabilizer). The hinged center section of a horizontal stabilizer that can be raised and lowered to change the angle of incidence of the horizontal tail (flying tail).

Stabilizer CenterSectionTorsion

Box

BRADING. The interlacing of yarns or tows into a tubular shape instead of a fabric

BULKHEAD. A heavy structural member in the fuselage to contain pressures or fluids or to disperse concentrated loads. A heavy circumferential frame that may or may not be entirely closed by a web.

EmpennagePressure Bulkhead

Rear View

WheelwellPressure Bulkhead

Rear View BUTTOCK LINE. A vertical reference line or plane parallel to the centerline of the airplane used to locate points or planes to the left or right of the airplane centerline.

Glossary of Terms


LBL BL0

RBL

CHEMICAL ETCHING. A process used to form a part from a sheet thicker than required while avoiding fatigue-inducing machining lines. The sheet is placed in a weak acid bath until areas not protected by an acid-resistant coating are etched away with great précising. Also called CHEMICAL MILLING.

CHORD PLANE, WING. The plane that defines the planform of the wing and around which the airfoil is figured. The wing chord plane scribes a line from the extreme point of the leading edge to the extreme point of the trailing edge, thus giving a datum line to measure incidence and dihedral.

Wing chord plane

Wing chord plane

CHORD (structural). Sometimes called a cap. A strong member that forms the edges of beam structures or heavy frames.

Chord

Chord CIRCUMFERENTIAL. A frame that is shaped to the fuselage.

Circumferential

CLAD. A 99% pure aluminum layer, molecular-bonded to the basic alloy by rolling while heated.

99% Pure AL

Basic Alloy CLIP. Sometimes called bracket. Usually a small angle used to attach lightweight parts such as wing clamps.

COMPOSITE MATERIAL. Composites are considered combinations of material differing in composition or form. The constituents retain their identifies I the composite; that is, they do not dissolve or otherwise merge completely into each other although they act together. Normally, the components can be identified physically.

COVE LIP DOOR. A movable door on the under surface of the wing, hinted at the rear spar, that lifts upward when the flaps are lowered. These doors allow high-pressure air to flow through the main flap slots. Used on KC-135, 707, and 720 airplanes.

Cove Lip Door

COWL PANEL. The hinged and removable sides of the pod or nacelle that cover an engine.

Cowl panel COWLING. A removable covering placed around all or part of an engine.

DAMAGE CONTAINMENT FEATURES. Specific design characteristics of a load-carrying member within the structure which are introduced in order to arrest or sufficiently a crack and enhance the capability to carry the applied loads in the event of partial failure of that member.

DECK. The horizontal floor in the control cabin or passenger cabin. The horizontal structure to support fuselage tanks in the B-52 (fuel deck).

Glossary of Terms


Deck

DESIGN SERVICE GOAL, DSG. The period of time in flight hours/cycles/years, established at a design and/or certification that represents the initially anticipated operational life of the airplane, during which the principal structure will be reasonably free from fatigue damage.

DETAIL DESIGN POINT, DDP. An area within a PSE where fatigue cracking is likely to occur and where the damage tolerance assessment is made.

DIHEDRAL. The angle the wing chord plane makes with a horizontal reference plane.

WCP

HRL

Dihedral angle DIMPLE. A depression of the area around the edges of a hole in thin sheet to provide for a countersunk rivet.

Dimple

DOUBLER. A second sheet or plate installed next to the web or skin in a small area subject to high local loads to provide a double thickness of material. A tripler is a third sheet to provide three layers of material.

DRAG STRUT. A diagonal brace attached to the forward end of the landing gear trunnion and the lower end of the oleo strut. Absorbs drag loads during ground maneuvers and braking.

Drag strut

DRIVEN HEAD. The upset portion of a rivet shank that has been hammered flat by the bucking bar during installation.

Driven head DUTCH ROLL. A phenomenon peculiar to swept wing aircraft. A continuous combination of yaw and roll.

ELEVATOR. The hinged section of the horizontal stabilizer used to control pitch.

Elevator EMPENNAGE. The aft portion of an aircraft, usually consisting of a group of stabilizing planes or fins, to which control surfaces such as elevators and rudders are attached.

EXTRUSION. A part formed by squeezing the material through a die that has a hole cut to the desired cross-sectional shape of the part.

FAIRING. An auxiliary structural member shaped to provide a smooth flow of air and reduce drag.

FAYING SURFACE. A surface that fits, joins, or unites closely with an adjacent surface overlapping it.

FIBERS. A general term which has a long axis that is many times greater than its radius.

FILAMENT. A single fiber. This is the unit formed by a single hole in the spinning process.

FILLET. A filler that smoothes the angle formed by two intersecting surfaces and eliminates an abrupt change of direction. Used on forged or machined parts to prevent stress concentration at the “corner.” Used aerodynamically to eliminate angular joints between components.

Glossary of Terms


Fillet

FLAP, LEADING EDGE. Hinged section of the under side of the leading edge that, when extended prevents airflow separation over the top of the wing. Leading edge flaps hinge at the leading edge of the airfoil.

Flap

FLAP, TRAILING EDGE. Hinged section of the trailing edge of the wing that can be lowered and extended. When lowered, flaps increase airplane lift at low speeds.

Flap

FLAP TRACK. A steel track on which the main landing flaps operates by means of rollers. The curvature of the flap track determines the deflection and position of the landing flaps when they are extended.

FLAT PATTERN. The overall shape or outline of a sheet metal part before bending operations.

FLING TAIL. A horizontal stabilizer that can be moved to trim the airplane.

FLYING TAIL. A horizontal stabilizer that is movable and controllable. The entire horizontal tail angle of incidence can be changed to trim the airplane.

Horizontal tail movement, 727

FRAME. A circumferential structural member in the body that supports the stringers and skin. Used in semimonocoque construction. (see MONOCOQUE).

Frame

HAT SECTION. The cross-section shape of the stringers used in the fuselage. A common rolled shape that looks like a top hat with the brim curled up.

HI-SHEAR RIVET. Trade name for high-shear-strength steel fasteners used in the airplane where heavy loads are encountered. Installed with a swaged collar instead of being upset by a bucking bar. Used in shear applications.

Collar driven on

Hi-shear rivet HRL (horizontal reference line). Will sometimes refer to a water line or can be a special horizontal line to locate a particular plane or points in the airplane’s horizontal axis (see WATER LINE).

WL207.5

Water line 207.5 INBOARD. A term applying to the inside. An item nearest to the fuselage centerline (antonym: OUTBOARD).

INCIDENCE, ANGLE OF. The fixed angle at which the wing chord plane is set relative to the horizontal datum line of the aircraft. Sometimes erroneously called the angle of attack; angle or attach rightfully refers to the angle of the entire aircraft to relative wind. The angle of attack can be changed by the elevators on the horizontal tail surfaces.

Glossary of Terms


Incidence angle INTEGRAL MACHINING. The process of cutting components from solid metal. The stiffeners and ribs are machined integrally with the skin, eliminating rivet holes which can lead to high localized loading.

INTERCOSTAL. A small stabilizing beam between and at right angles to larger beams or bulkheads.

Intercostal

Beam

JIG. A structure which holds the component members of a particular assembly in exact relationship to each other, to ensure that the finished part is accurate and will be interchangeable with like parts.

LEADING EDGE FLAP. The hinged section on the underside of the leading edge of the airfoil. Extended, the leading-edge flap prevents airflow separation over the top of the wing.

LIMIT OF VALIDITY, LOV. The period of time, expressed in appropriate units (e.g., flight cycles), for which it has been shown that the established inspections and replacement times will be sufficient to preclude development of wide spread fatigue damage.

LIFT. Generated by an airfoil when the air has to travel a slightly greater distance as it skims the top of the wing than when passing beneath it. The difference in air pressure lifts the airplane upward.

LOCK BOLT. A high-strength steel fastener with a swaged collar on the shank for retention rather than a nut. Used in tension and shear applications.

Collar pressed on

Lock bolt LOFT LINE. The line or lines that establish and control the shape of an object so that all intersecting cutting planes are smoothly faired.

LONGERON. A principal longitudinal member of the framing of an aircraft fuselage or nacelle. Usually continuous across a number of points of support.

Longeron

MACH NUMBER. A number representing trhe ratio of the speed of a body to the speed of sound in the surrounding atmosphere. For subsonic speed the mach number is less than 1 and for supersonic speed it is greater than 1.

MLG. Abbreviation for main landing gear.

MONOCOQUE. A single-shell construction in which the skin carries all shear and bending stresses. In semimonocoque construction, shear and bending loads in the skin are transmitted to stringers and frames.

Stringer

Skin

MULTIPLE ELEMENT DAMAGE, MED. A source of widespread fatigue damage characterized by the simultaneous presence of fatigue cracks in similar adjacent structural elements.

MULTIPLE LOAD PATH, MLP. Identified with redundant structures in which (with the failure of individual elements) the applied loads would be safely distributed to other load-carrying members.

MULTIPLE SITE DAMAGE, MSD. A source of widespread fatigue damage characterized by the simultaneous presence of fatigue cracks in the same structural element (i.e., fatigue cracks that may coalesce with or without other damage leading to a loss of required residual strength).

NACELLE. A streamlined enclosure that covers the engine, sometimes called a POD.

Nacelle

NONCONFORMANCE. Any material, part, or product in which one or more characteristics do not conform to the requirements specified in the contract, specification, engineering drawing, or other applicable product description.

OIL CAN. A term commonly used to describe a buckling or wrinkling in the metal of an airplane. The skin normally should be smooth.

Glossary of Terms


OLEO STRUT. A main weight-carrying strut in the landing gear that absorbs the shock of landing by the flow of oil through an orifice in the cylinder of the strut.

Oleo

PITOT-STATIC. An airspeed indicating system that operates from ram air pressure in the pitot tube and static pressure of the atmosphere. Gives an airspeed reading that is corrected for altitude.

PLUG-TYPE DOORS. Airplane doors designed larger than the doorway, so they will be held in space by pressure. A required design for airplane doors in passenger cabins.

POD. A term sometimes used for engine nacelle. Indicates an enclosure such as the boom operator’s pod on the KC-135 that encloses the boom operator and equipment in a streamlined fairing.

Pod

POISSON'S RATIO EFFECT. A normal strain is that which is associated with a normal stress; a normal strain occurs in the direction in which its associated normal stress acts. Normal strains that result from an increase in length are designated as positive (+) and those that result in a decrease in length are designated as negative (-).

Under the condition of uniaxial loading, strain varies directly with stress. The ratio of stress to strain has a constant value (E) within the elastic range of the material, but decreases when the proportional limit is exceeded (plastic range). Axial strain is always accompanied by lateral strains of opposite sign in the two directions mutually perpendicular to the axial strain. Under these conditions, the absolute value of a ratio of lateral strain to axial strain is defined as Poisson's ratio. For stresses within the elastic range, this ratio is approximately constant. For stresses exceeding the proportional limit, this ratio is a function of the axial strain and is then referred to as the lateral contraction ratio. Information on the variation of Poisson's ratio with strain and with testing direction is available in reference 1.

Under multiaxial loading conditions, strains resulting from the application of each directional load are additive. Strains must be calculated for each of the principal directions taking into account each of the principal stresses and Poisson's ratio.

PRESSURE WEB. A web that seals an area to retain cabin pressurization

PRINCIPAL STRUCTURE ELEMENT, PSE. An element that contributes significantly to the carrying of flight, ground or pressurization loads, and whose integrity is essential in maintaining the overall structural integrity of the airplane.

RADOME. Coined term for radar dome. A nonmetallic streamlined fairing to cover the radar sweep.

Radome

REPAIR. A procedure that reduces, but not completely eliminates, a nonconformance and which has been reviewed and approved by the MRB (in-plant) or DER (in the field). The purpose of the repair is to reduce the effect of the nonconformance. Repair is distinguished from rework in that the characteristic after repair still does not completely conform to the applicable engineering drawing, specification, or contract requirements. Examples: Mislocated Holes Shop Error Plugged Holes Shop Error Oversized Fasteners Hi-Lok Replacement Use As Is Structurally Acceptable Nonconformance

REWORK. A procedure applied to a nonconformance that will completely eliminate it and result in a characteristic that conforms completely to the engineering drawings, specifications, or contact requirements

RIB. A fore and aft member of an airfoil structure (wing or aileron) of an aircraft used to give the airfoil section its form and to transmit that load from the skin to the spars.

Rib ROVING. A number of yarns or tows collected into parallel bundle without twisting.

Glossary of Terms


RUDDER. A hinged or movable auxiliary airfoil, attached to the vertical fin, that controls yaw.

SAFE LIFE. of a structure is that number of events such as flights, landings, or flight hours, during which there is a low probability that the strength will degrade below its design ultimate value due to fatigue cracking.

SCATTER FACTOR. A life reduction factor used in the interpretation of fatigue analysis and fatigue test results.

SECTION. Any of the large subassemblies of the airplane that are built separately and then joined to form the complete airplane. The airplane is built in sections to ease production and handling problems.

Section 41 SEMI-MONOCOQUE. A stressed-skin construction that transmits loads in the skin to stringer and frames.

SHEAR STRAIN. When an element of uniform thickness is subjected to pure shear, each side of the element will be displaced in opposite directions. Shear strain is computed by dividing this total displacement by the right angle distance separating the two sides.

SINGLE LOAD PATH, SLP. Where the applied loads are carried through a single member, the failure of which would result in the loss of the structural capability to carry the applied loads.

SKIN. The outside covering of an aircraft.

SLAT. A movable auxiliary airfoil attached to the leading edge o the wing. When closed, it forms part of the normal counter of the wing; when opened, it forms a slot and increases lift.

Slat SLOT. An elongated passage through a wing whose primary function is to improve the airflow over the wing at high angles of attack.

Slot

SPAR. A principal spanwise beam in the structure of a wing, stabilizer, rudder, or elevator. It is usually a primary load-carrying member in the structure.

Rear spar

Front spar SPOILER. A hinged panel on the upper surface of a wing that “spoils” wing lift when raised. Left and right spoilers can be raised alternately for high-speed lateral control or can be raised together as speed brakes during landing.

Spoiler

STALL. The aerodynamic point reached when the airflow across the top of the airplane wing breaks away from the surface. The massively turbulent wake that is created at stall speed causes the airplane to lose altitude until the pilot can restore the angle of attack to a low value.

STABILIZER. A fixed horizontal tail surface that maintains stability around the lateral axis of an aircraft.

STATION LINE. All parts of an airplane are identified by a location or station number in inches from a beginning point. Station lines in the fuselage start forward of the nose; those for the wing usually start at the centerline of the fuselage. This forms a locating system that divides the aircraft cross-sectionally into a series of reference planes at right angles to the centerline of the aircraft.

Glossary of Terms


Window No. 1

STA130 17

8

239.

5

344

FWD pressurebulkhead

Nose compartmentfwd access door Nosegear door

STIFFENER. A metal part, other than flat sheet, formed or extruded and used in the framing of a structure to provide rigidity.

Stiffener

STRAIN. Strain is the change in length per unit length in a member or portion of a member. As in the case of stress, the strain distribution may or may not be uniform in a complex structural element, depending on the nature of the loading condition. Strains usually are present also in directions other than the directions of applied loads.

STRAIN RATE: Strain rate is a function of loading rate. Test results are dependent upon strain rate, and the ASTM testing procedures specify appropriate strain rates. Design properties in this Handbook were developed from test data obtained from coupons tested at the stated strain rate or up to a value of 0.01 in./in./min, the standard maximum static rate for tensile testing materials per specification ASTM E 8.

STRAND. A general and somewhat imprecise term. It usually refers to a bundle or group of untwisted filaments, but it has also been used interchangeably with fiber and filament.

STRESS. The term "stress" implies a force per unit area and is a measure of the intensity of the force acting on a definite plane passing through a given point. The stress distribution may or may not be uniform, depending on the nature of the loading condition. For example, tensile stresses identified by Equation ft = P/A (tension) are considered to be uniform. The bending stress determined from Equation fb = My/I = M/Z (bending) refers to the stress at a specified distance perpendicular to the normal axis. The shear stress acting over the cross section of a member subjected to bending is not uniform. (Equation fs = S/A (average direct shear stress) gives the average shear stress.)

STRETCH FORM. A method used to shape skins or parts by stretching the flat sheet over a die to provide the shape.

STRINGER. Longitudinal members in the fuselage or spanwise members in the wing to transmit skin loads into the body frames or wing ribs.

Body stringer

Wing stringer

STRUT. A structural member that braces loads.

Strut

TAB. A small, hinged, auxiliary control surface attached to a primary control surface such as an aileron, rudder, or elevator. When deflected, it moves the primary surface to which it is attached. The primary surface will react in the direction opposite the control tab’s deflection.

TAPE. a collection of parallel filaments (often made from two) in which the filaments are held together with a binder (usually the composite matrix). The length of the tape, in the direction of the fibers, is much greater than the width, and the width is much greater than the thickness.

ELONGATION AND REDUCTION OF AREA. Elongation and reduction of area are measured in accordance with specification ASTM E 8.

TOW. An untwisted bundle of continuous filaments, usually with a specific count (such as 12,000 filaments).

Glossary of Terms


Rudder

Tab

Tab

TRAILING EDGE. The hinged section of the trailing edge of the wing. Trailing-edge flaps can be lowered and extended to increase airplane lift at low speeds.

TRUCK. The portion of the main landing gear that is composed of a swiveling beam with an axle and two wheels on each end.

Truck

VENTRAL FIN. A stabilizing surface attached to the bottom of the fuselage near the tail.

Ventral fin VERTICAL FIN. Sometimes referred to as vertical stabilizer. It is fixed to provide directional stability. The trailing edge is hinged to form the rudder.

Vertical fin

VORTEX GENERATOR. A device used on the wings and tail surfaces to decrease drag caused by the separation of the air flowing over the flight surfaces. Vortex generators appear as a row of small metal tabs set at angles to the air stream. The vortex formed by the tabs pushes the air down to the skin of the flying surface and delays drag producing separation.

Vortex generators areminiature wings and areinstalled in pairs

Vortex

Boundary layer

Wing skinLow-velocity air

Directionof flow

Low-velocity air

High-velocity air(low pressure) Vortex is

formed here

WATER LINE. A reference line or horizontal plane parallel to the ground used to locate points vertically.

Water line 207.5

WL207.5

WEB. A thin-gauge plate of sheet, when supported by stiffening angles and framing, provides great shear strength for its weight. Used in many applications throughout an aircraft because of its strength-to-weight ratio.

Rib web

Spar web

Glossary of Terms


WIDESPREAD FATIGUE DAMAGE, WFD. WFD in a structure is characterized by the simultaneous presence of cracks at multiple structural details that are of sufficient size and density whereby the structure will no longer meet its damage tolerance requirement (i.e., to maintain its required residual strength after partial structural failure).

WINGLET. A wing tip that is moved up or down to increase or reduce lift.

WOVEN FABRIC. A planar material made by interlacing yarns or tows in various specific patterns.

YARN. A twisted bundle of continuous filaments, hence a twisted tow. It is often used for weaving.

Symbols


A cross-section area Aeq stringer gross area Aen stringer net area Asg skin gross area Asn skin net area c distance from the bending neutral axis to the extreme fiber e strain ec strain corresponding to/,,, without considering local instability. em actual extreme fiber strain ebl strain at an intermediate fiber ecrit critical strain which results in local instability epu ultimate plastic strain E elastic modulus F allowable stress f applied stress fb apparent extreme fiber stress fbl actual bending stress at an intermediate fiber fm actual extreme fiber stress fo intercept stress in Cozzone trapezoidal stress distribution Fb aAllowable apparent extreme fiber stress Fcu ultimate compressive strength, Fcu. For the purpose of this analysis, Fcu is

assumed to be equal to Ftu. Fcy compressive yield strength Fm allowable actual extreme fiber stress Ft panel tension gross area design value ft panel tension gross area stress Fte allowable stringer tensile net area stress at panel failure strain fte stringer tensile net area stress at panel failure strain Ftp tensile proportional limit stress. Ftp is given by Ftp = F(0.005)(1).") Fts allowable skin tensile net area stress at panel failure strain fts skin tensile net area stress at panel failure strain Ftu ultimate tensile strength Fty tensile yield strength HOF hole-out factor l moment of inertia K section shape factor Kff material efficiency factor M applied moment Mr limiting resisting moment, Mr is the moment at which fm = Fm and fb = Fb ni initial shape factor of the stress-strain curve nu ultimate range shape factor of the stress-strain curve Q first moment of area. If not otherwise noted, it is about the principal axis about

which the resisting moment is calculated. u, v principal axes y distance from the neutral axis to an intermediate fiber

Symbols


γ material plasticity factor, γ. γ Is defined by γ = fo/Ftu γ is equal to one for a perfectly plastic material and equal to zero for a perfectly elastic (brittle) material. γ can be calculated using the plastic bending: γ = (fb – Ftu) / (Ftu(K-1) where fb is the apparent Mc/I stress at an actual extreme fiber stress, fm equal to Ftu for any convenient K value other than one.

Definitions


Symbol Definition

A, B, C designations for high-strength aluminum alloys

Cp plasticity correction factor for web buckling stress

de effective hole diameter

E modulus of elasticity

f1, f2 maximum principal stresses

fs shear stress

fscr buckling shear stress

fs net net area shear stress

fs allowable shear stress

Fscr allowable buckling shear stress

Fscr-el allowable buckling shear stress, uncorrected for plasticity

Fsu material ultimate shear strength

Ftu material ultimate tensile strength

Fty material tensile yield stress

h distance between chord c.g.’s

I area moment of inertia

k diagonal tension factor

Ken net area efficiency factor

Kep pocket efficiency factor

Krest edge restraint factor

L longitudinal grain direction

L + 45° 45 degrees to the longitudinal grain direction

LT long transverse grain direction

L-T shear plane is normal to the longitudinal grain direction and loading is along the long transverse grain direction

Q area first moment

Definitions


R1 correction factor B value allowables

R2 correction factor for portal frame effect

Rch horizontal edge restraint coefficient

Rst vertical edge restraint coefficient

S fastener pitch

t web basic gage

t1 thickness of the stiffener free flange

t2 thickness of the stiffener outstanding flange

tp web pad thickness

tst stiffener web leg thickness

T-L shear plane is normal to the long transverse grain direction and loading is along the longitudinal grain direction

V shear load

Vcr buckling shear load

VF failure shear load

VP shear load due to portal frame

W1 width of the stiffener free flange

W2 width of the stiffener outstanding flange

W3 width of the stiffener web leg

XD 2024 protruding head solid rivet

XTH alloy steel protruding head Hi-Lok

XZK 2017-T3 protruding head rivet

YHY titanium shear hex-head Hi-Lok

Acronyms


AC airworthiness circular AD accidental damage BCA Boeing Commercial Airplanes BMS Boeing Material Specifications BVID barely visible impact damage Cd cadmium CFD computational fluid dynamics DBT design/build team DPA digital pre-assembly DSO design service objective ED environmental damage FAA Federal Aviation Administration FAR Federal Aviation Regulations FD fatigue damage FEM finite element method FRF fatigue reliability factor HSLA high strength low alloy IPT integrated product teams IWS integrated work statement JSF Joint Strike Fighter KBE Knowledge-Based Engineering MED multiple element damage MLG main landing gear MSD multiple site damage NDI non-destructive inspection SS stainless steel VID visible impact damage WFD widespread fatigue damage

Acronyms


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1 glossary

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