This article describes the results of several case history studies of the failure of polymer-matrix composite components to provide not only some representative types of failures that can encounter, but also to provide some insight into the investigative process. These case histories deal mainly with structures that exhibit an initial material and/or manufacturing defect or failures that are most prevalent and most easily solved. The components include helicopter rotor blade, composite wing spar, and aircraft rudder.

This article provides information on the applications of fiber-reinforced composites in commercial and military aircrafts. It tabulates the composite components in various types of aircraft. The applications of the composites in the components of Boeing 727, 737, 757, 767, 777, and 777-200 are schematically illustrated.

Mechanical and environmental loadings cause a variety of failure modes in composites, including matrix cracking, fiber-matrix debonding, delamination between plies, and fiber breakage. This article summarizes visual analysis and nondestructive testing methods for the failure analysis of composites. These methods include radiography, ultrasonic techniques, acoustic emission, and thermograph. The article also provides information on destructive test techniques.

This article provides non-proprietary and non-competition-sensitive information related to aircraft applications. It presents an overview of reliability and commonly used measurements. Failure modes that cause the negative performance are reviewed based on many types of sources. These include manufacturer service bulletins, reliability and customer service departments, literature reviews, demonstration programs, in-service evaluations, design guides, and surveys of commercial and military aircraft maintenance organizations. The article also describes lessons learned while attempting to avoid overlapping maintainability, reparability, and materials choice.

The aluminum alloy 7099 is a Kaiser aluminum high-strength Al-Mg-Zn-Cu alloy with zirconium that offers a less quench-sensitive alloy for properties in thicker sections for airframe structures such as wing ribs, spars, and skins, as well as fuselage frames and floor beams. This datasheet provides information on key alloy metallurgy and processing effects on mechanical properties of this 7xxx series alloy.

This article discusses the requirements for designing repairable composite structures such as a honeycomb sandwich panel construction and integrally stiffened co-cured composite structures. It reviews the general and specific design guidelines for bolted or riveted repairs and adhesively bonded repairs of the composite structures. The article presents several examples to illustrate how these repairs can be achieved.

This article discusses bismaleimide (BMI) chemistry and the use of BMI in composites. An analysis of the applications illustrates how the advantages of BMIs have been exploited and perhaps suggests how these advantages might be extended to other applications. The article describes the mechanical properties of BMI composites. BMIs suitable for resin transfer molding processing are provided. The article concludes with information on the elevated-temperature applications of 5250-4 BMI system.

This article presents the damage tolerance criteria for military composite aircraft structures to safely operate the structures with initial defects or in-service damage. It describes the effects of defects, such as wrinkles in aircraft structures, and the reduction in compressive strength and tensile strength. The article reviews low velocity impacts in aircraft structures in terms of resin toughness, laminate thickness, specimen size and impactor mass, and post-impact fatigue. It explains the tension strength analysis, such as linear elastic fracture mechanics and R-curve methods, to predict the residual strength of the structures.

Automated tape laying is a mature process used in both commercial and military aircraft applications. This article provides a brief history of the process and describes the use of commercially available flat and contour tape-laying equipment. It discusses the advantages and disadvantages of the tape laying. The article describes the various components of a ten-axis gantry-type tape laying machine and the tape laying process. It provides a discussion on typical material types and forms for tape laying and provides information on design guidelines for tape laying.

Alloy 7097 is a quench insensitive Al-Mg-Zn-Cu-Zr alloy engineered for the most advantageous combination of strength, corrosion resistance, and fracture toughness in thick structural applications. This datasheet provides information on key alloy metallurgy of alloy 7097 and processing effects on mechanical properties of alloy 7097-T7651 plate.

Advanced thermoplastic composites possess impact resistance, fracture toughness, and elevated temperature endurance properties due to their melt-fusible nature. This article presents the material options available for thermoplastic composites such as pseudothermoplastics, post-impregnated thermoplastics, and true thermoplastics. It describes the processing methods of thermoplastic composites, including weaving, seaming, autoclaving, preconsolidation, roll consolidation, roll forming/pultruding, thermoforming, press forming, hydroforming, and diaphragm forming. The article provides information on different types of joints, namely, fastened, adhesive bonded, dual polymer bonded, co-consolidated, and welded joints. It explains the joining methods of thermoplastic composites, such as press forming, diaphragm forming, autoclaving, ultrasonic welding, resistance welding, and induction welding.

This article describes the commonly observed forms of airplane corrosion, namely: general corrosion, exfoliation corrosion, pitting corrosion, microbiologically induced corrosion, galvanic corrosion, filiform corrosion, crevice corrosion, stress-corrosion cracking, and fretting. It discusses the factors influencing airplane corrosion from the manufacturing perspective: design, manufacturing, and service-related factors. The article explains the collection of corrosion data and provides an overview of the implementation and evolution of airline corrosion prevention and control programs and directions being considered in the design for corrosion prevention of airplanes.

Environmental effects of ground and flight environments, including temperature extremes, damage by chemical fluids, moisture, and so forth, affect the durability of polymer-matrix composites. This article provides information on corrosion control methods in aircraft structures. It discusses the design considerations for sealants in joints. The article describes the common methods to seal aircraft structures: fay surface, fillet, butt joint, channel, brush, and form-in-place seals. It discusses the surface preparation and application method of primer and topcoat systems. Primer and paint application equipment as well as sealant application equipment are reviewed.

Composite bonded repair technology is based on the use of advanced composite repairs or reinforcements that are adhesively bonded to a damaged structure. This article discusses the key steps that are normally encountered in the design, certification, and application of an adhesively bonded repair. Some examples of successful repairs to military aircraft are also discussed.

The primary motivation for the insertion of metal-matrix composites (MMCs) into aeronautical systems is the excellent balance of specific strength and stiffness offered by MMCs. This article provides information on the aerostructural, aeropropulsion, and aeronautical subsystem applications of MMCs. The applications include ventral fin, fuel access door covers, helicopter blade sleeve, fan exit guide vane, nozzle actuator piston rod, nozzle actuator links, T-1 racks, and hydraulic manifold.

This article schematically illustrates the basic types of drafts used in forging design, including outside draft, inside draft, blend draft, natural draft, shift draft, and back draft. The amount of draft, or the draft angle, is designated in degrees and is measured from the axis of a hammer or press stroke. The article illustrates the measurement of draft angle by describing the designs of forgings produced in equipment with vertical and horizontal rams. The use of excessive amounts of draft usually results in an increase in overall cost. The article describes various alternatives for reducing or eliminating draft. It provides a checklist citing major items that should be coordinated with a designer's review of draft.

This article is an atlas of fractographs that helps in understanding the causes and mechanisms of fracture of wrought aluminum alloys and in identifying and interpreting the morphology of fracture surfaces. The fractographs illustrate the corrosion-fatigue fracture, fatigue striations, tension-overload fracture surface, ductile fracture, cone-shaped fracture surface, intergranular crack propagation, transgranular crack propagation, stress-corrosion cracking, hydrogen damage, and grain-boundary separation of these alloys. Fractographs are also provided for a forged aircraft main-landing gear wheel and actuator beam, an aircraft wing spar, a fractured aircraft propeller blade, shot peened fillet, an aircraft lower-bulkhead cap, and clevis-attachment lugs.

This article describes the influences of the operational environments of U.S. Navy aircraft during corrosion-control process. The most widely used materials in airframe structures and components, such as aluminum, steel, titanium, and magnesium alloy systems, are reviewed. The article provides information on the inspections steps, corrosion-control issues, and corrosion-prevention strategies for naval aircraft. It contains a table that lists typical locations of corrosion on the aircraft. The article also provides examples of aircraft corrosion damage.

This article provides information on the thermoplastic resins used as matrix materials for continuous fiber reinforced composites. It focuses on the materials that are suitable for fabrication of structural laminates and used for aerospace applications. The article provides a discussion on the background, categories, characteristics, product forms, properties, cost benefits, and processing techniques of thermoplastic resins. Strategies that have been advanced to deal with impregnation difficulties are also discussed.

The prepreg hand lay-up process is a versatile, reliable, cost-effective, and high quality process for fabricating large or small components. This article discusses the technique characteristics and applications of the process. It describes the stages involved in the process of lay-up, namely, lay-up definition, ply-kit cutting, layup, debulking, and preparation for curing. The article concludes with a discussion on the component properties and design guidelines of the prepreg hand lay-up process.