Par 205 Page 14 TABLE 2-2. EFFECTS OF MOISTURE AND FUNGI ON VARIOUS MATERIALS Part of Material Effects of Moisture and Fungi Fiber: washers, supports, etc. Moisture causes swelling that can lead to misalignment and binding of parts. Destroyed by fungi.
Fiber: terminal strips and insulators Electrical leakage paths are formed causing flashovers and crosstalk.
Insulating properties are lost. Destroyed by fungi.
Laminated plastics: terminal strips and boards, switchboard panels, etc., tube sockets and coil forms Insulating properties are lost. Leakage paths cause flashovers and crosstalk. Delamination occurs and fungi grow on surface and around edges. Expansion contraction under extreme temperature changes.
Molded plastics: terminal boards, switchboard panels, connectors, tube sockets and coil forms, etc.
Machined, sawed, or ground edges of surfaces support fungi, causing shorts and flashovers. Fungi growth can reduce resistance between parts mounted on plastic to such an extent that the parts are useless.
Cotton linen, paper, and cellulose derivatives: insulation covering webbing, belting, laminations, dielectrics, etc.
Insulating and dielectric properties are lost or impaired, causing arcing, flashovers, and crosstalk. Destroyed by fungi.
Wood: cases, houses, plastic fillers, masts, etc.
Dry rot, swelling, and delaminated housings caused by moisture and fungi.
Leather: straps, cases, gaskets, etc.
Moisture and fungi destroy tanning and protective materials, causing deterioration.
Glass: lenses, windows, etc. Fungi grow on organic dust, insect track, insect feces, dead insects, etc. Dead mites and fungi growth on glass obscure visibility and corrode nearby metal parts.
Wax: for impregnation Fungi-inhibiting waxes that are not clean support the growth of fungi, cause destruction of insulating and protective qualities, and permit entrance of moisture that destroys parts and unbalances electrical circuits.
Metals High temperature and moisture vapor cause corrosion, etching of surfaces, and oxidation. This interferes with the operation of moving parts, screws, etc., and causes dust between terminals, capacitors, plates, or air conductors, etc., which in turn leads to noise, loss of sensitivity, and arc-over.
Metals, dissimilar Metals may have different corrosion potentials. When moisture is present, one of the metals (anode) corrodes.
Soldered joints Residual soldering flux on terminal boards holds moisture which speeds up corrosion and growth of fungi.
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206. TYPES OF CORROSION.
a. General. Many different forms of corrosion occur on avionics equipment, depending on the type of material, configuration of the materials, and their environment. The rate and magnitude of the corrosion attack is also dependent upon those same materials and environment.
A corrosion attack on equipment may involve several types of corrosion occurring simultaneously. This section describes the individual types of corrosion common to most avionics equipment.
b. Uniform Surface Corrosion. Uniform surface corrosion is probably the most common type of corrosion and results from a direct chemical attack on a metal surface. This type of corrosion appears uniform because the chemical elements that make up an alloyed metal are different and thereby become anodes and cathodes. These anodes and cathodes are very small and constantly shift from one area of the surface to another. A dull or etched surface is usually the first indication of uniform surface corrosion. Continued attack is followed by roughness and a frosty or powdered surface.
c. Crevice Corrosion. Crevice corrosion, also called concentration cell corrosion, occurs between the two mating surfaces in the presence of an electrolyte that has a different concentration/potential from one area to another. The electrolyte inside the crevice has a lower oxygen level and a higher metal ion concentration than the area just outside the crevice. As a result, the metal surfaces, even though they may be of the same material, have different potentials, and corrosion occurs. Figure 2-2 shows evidence of crevice corrosion on a lower fuselage skin at an antenna mounting. This type of corrosion may also occur when one of the mating surfaces is nonmetallic. There are three types of crevice/concentration cell corrosion:
metal ion concentration cells, oxygen concentration cells, and active passive cells.
(1) Metal Ion Concentration Cells. Stagnant electrolytes under mating/faying surfaces normally have a high concentration of metal ions compared to the metal just outside the mating/faying surface. The area of high metal ion concentration will be cathodic, while the area with a lower concentration will be anoxic and suffer corrosion.
(2) Oxygen Concentration Cells. Electrolytes normally contain dissolved oxygen.
Stagnant electrolytes under mating/faying surfaces contain less dissolved oxygen and are more anoxic than the adjacent area outside the mating surface. Corrosion occurs in the area of lower oxygen concentration.
(3) Active Passive Cells. Metals which depend on tightly adhering oxide films for corrosion protection, such as an anodized surface on aluminum, are prone to a rapid corrosion attack by active passive cells. An active passive cell occurs when the oxide film is broken from a scratch. The difference in potential between the small area of exposed parent metal (anoxic area) and the larger oxide film (cathodic area) is high and the onset of corrosion is rapid.
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d. Pitting Corrosion. Pitting corrosion is a severe form of concentrated cell corrosion and is localized to a specific area. Pitting corrosion can be found on thin sheets of metal, such as plated PCB paths. The attack can be so severe that perforation of the plated PCB paths can occur.
Pitting usually occurs along grain boundaries and at porous finished areas on the metal. Porous gold plating on copper contacts is a common location for pitting corrosion. The plating pores create small corrosion cells that continue to expand and deepen until a pit is created.
FIGURE 2-2. EVIDENCE OF CREVICE CORROSION ON LOWER FUSELAGE SKIN
AT AN ANTENNA MOUNTING
e. F retting Corrosion. Fretting corrosion occurs when there is slight relative movement between two materials (usually metals) and an electrolyte is present. This corrosion is typical of close fitting, highly loaded interfaces. Fretting corrosion can occur on all metals, with aluminum, stainless steel, and titanium alloys being the most susceptible. These metals depend on an oxide surface film to inhibit further corrosion. With small movements between the two mating surfaces under pressure, the exposed oxide surface film is abraded away, exposing new parent metal. This new metal surface oxidizes again and the cycle repeats. The oxides that were abraded away locate themselves in the crevices of the parent metal. The oxides are harder than the parent metal, and, as the abrasion continues, they will act as an abrasive grit which further attacks the parent metal.
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f. Galvanic Corrosion. Galvanic corrosion occurs when different metals are in contact with each other in the presence of an electrolyte. Galvanic corrosion is characterized by a buildup of corrosion deposits on the mating active (anoxic) surface. The rate of corrosion of a galvanic couple is a function of the difference between the reactivity of the metals. The galvanic series for metals with saltwater as the electrolyte is outlined in Table 2-3. The farther apart two metals are on the galvanic series chart, the faster the active (anode) metal will corrode in the presence of the electrolyte. In contrast, the closer the two metals are on the galvanic series chart, the slower the active (anode) metal will corrode in the presence of the electrolyte.
Par 206 Page 18 TABLE 2-3. GALVANIC SERIES OF METALS AND ALLOYS IN SEAWATER
CORRODED END (ANOXIC, ACTIVE, OR LEAST NOBLE) Magnesium Alloys Zinc (plate) Beryllium Cadmium (plate) Uranium (depleted) Aluminum Alloys Indium Tin (plate) Stainless Steel 430 (active) Lead 1010 Steel Cast Iron Stainless Steel 410 (active) Copper (plate) Nickel (plate) AM 350 (active) Chromium (plate) Stainless Steel 350, 310, 304 (active) Stainless Steel 430, 410 (passive) Stainless Steel 13-8, 17-7 PH (active) Brass, Yellow, Naval Stainless Steel 316L (active) Bronze 220 Copper 110 Stainless Steel 347 (active) Copper-Nickel 715 Stainless Steel 202 (active) Monel 400 Stainless Steel 201 (active) Stainless Steel 321, 316 (active) Stainless Steel 309, 13-8, 17-7 PH (passive) Stainless Steel 304, 301, 321 (passive) Stainless Steel 201, 316L (passive) Stainless Steel 286 (active) AM355 (active) Stainless Steel 202 (passive) Carpenter 20 (passive) AM355 (passive) Titanium Alloys AM350 (passive) Silver Palladium Gold Rhodium Platinum Carbon/Graphite
PROTECTED END (CATHODIC, PASSIVE, OR MORE NOBLE)
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g. Stress Corrosion. Stress corrosion or stress corrosion cracking occurs when stresses on a metal part and corrosion combine to produce damage greater than either one applied separately. The stresses on the part can be internal (residual) or externally applied. Stress corrosion cracking of metal parts occurs along (intergranular) or across (transgranular) boundaries. Stress corrosion failures can be catastrophic and occur without warning. For example, cracking can occur in stressed copper alloys exposed to ammonia and its compounds.
h. Corrosion Fatigue. Corrosion fatigue is normal fatigue combined with corrosion.
Normal fatigue, in a non-corrosive environment, is caused by repeated stress cycles at a level below the maximum stress the material can withstand. The fatigue (endurance) limit is the maximum cyclic stress at which a material will not sustain any fatigue damage (i.e., will not fracture). The combination of corrosion and fatigue reduces the fatigue limit of a material.
Corrosion fatigue will eventually produce a failure regardless of how minimal the applied stress.
i. Intergranular Corrosion. Intergranular corrosion is a chemical attack that occurs at the grain boundaries of a metal. A highly magnified view of a metal surface shows individual grains. Along the grain boundaries of the primary metal are individual grains of the metallic elements that make-up the alloy. These other metals have a different corrosion potential than the primary metal. Often, the grain boundaries are anoxic and tend to corrode more easily than the grains of the primary metal. When an electrolyte is present, rapid selective corrosion at the grain boundary occurs.
j. Exfoliation Corrosion. Exfoliation corrosion is an advanced form of intergranular corrosion. Exfoliation corrosion causes the metal grains to separate at the grain boundaries due to the force of the expanding corrosion products. This type of corrosion is most often visible as a swelling or lifting of an exposed edge in extruded sections of metal. It is primarily found in aluminum sheets around steel fasteners.
k. Nonmetallic Deterioration. Nonmetallic materials also deteriorate. This deterioration includes: swelling, distortion, disintegration, cracking, out gassing, and changes in electrical characteristics. The deterioration is caused by a change in the environment of the avionics equipment. These changes include: weather, moisture intrusion/entrapment, heat, ultraviolet (UV) light, fungal growth, etc.
207 through 300. RESERVED.
Par 301 Page 20 CHAPTER 3. CORROSION CONTROL PROGRAM AND INSPECTION
301. GENERAL. Investigations over the past ten years have revealed that corrosion is a major factor in avionics equipment failures. As much as 20 percent of commercial/general aviation avionics failures are attributable to corrosion, and that figure rises to between 30 and 40 percent for the military. This excessive failure rate continues despite continued improvement in the overall reliability of avionics equipment and systems. The scope of this problem outlines the need for an effective preventive maintenance program.
FIGURE 3-1. DUST AND LINT ACCUMULATION IN THE CROWN AREA
302.
PREVENTIVE MAINTENANCE PROGRAM.
a. Program Requirements. Successful avionics cleaning and corrosion prevention/control efforts depend on a coordinated, comprehensive preventive maintenance program. Everyone involved with the operation, repair, and maintenance of avionics equipment must take an all hands approach to cleaning, inspection, and corrosion prevention and control.
Figure 3-1 shows dust and lint accumulation in the crown area. The basic philosophy of a preventive maintenance program should consist of the following:
(1) Personnel adequately trained in the recognition of corrosion, including conditions, detection and identification, cleaning, treatment, and preservation;
(2) Thorough knowledge of corrosion identification techniques;
(3) Proper emphasis on the concept of all hands responsibility for corrosion control;
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(4) Inspection for corrosion, deteriorated seals, and proper routing on a scheduled basis;
(5) Routine cleaning of all wiring and the exterior surfaces of components;
(6) Keeping drain holes open;
(7) Early detection and repair of damaged protective coatings;
(8) Prompt corrosion treatment after detection;
(9) Accurate record keeping and reporting of material or design deficiencies; and
(10) Use of appropriate materials, equipment, and technical publications.
b. Corrosion Prevention Philosophy. Corrosion and environmental conditions are natural phenomena that adversely affect avionics equipment. Although they can never be totally eliminated, the problems these phenomena cause can be minimized so that they are more manageable. This can be achieved only by understanding the equipment failure mechanisms, implementing a preventive maintenance program, and using corrosion control techniques and materials.
303. CORROSION-PRONE AREAS.
a. General. There are certain corrosion-prone areas common to all aircraft. For example, bilge areas are particularly susceptible to moisture intrusion/entrapment. The bilge area is where cables run, and where wire bundles, coaxial cables, lights, and antennas are installed. It is almost impossible to prevent moisture intrusion/entrapment in these areas. Other corrosion-prone areas include areas in and around the engine exhaust, battery compartments, lavatories, buffets, galleys, entrances at cargo and passenger doors, and wheel wells and landing gear.
b. Moisture and Other Fluid Intrusion Sources. Moisture, fluid intrusion, and fluid movement within the aircraft are caused by many factors, including:
(1) The flexibility of aircraft structure, which prevents complete and effective airframe sealing at skin joints and around fasteners;
(2) Numerous openings, such as equipment bay doors, access panels, ducts, and static pressure sensors, which can allow moisture intrusion;
(3) Moisture from many sources, such as rain and aircraft wash, and fluids from leaking hydraulic, fuel, oil, and coolant lines; and
(4) Moisture and fluid migration within the aircraft along air condition ducts, fuel and hydraulic lines, and cable and wire bundles. As a result of these conditions, moisture and other fluids can enter, migrate, and be trapped in areas of the aircraft where avionics equipment may be installed, which are normally considered protected.
Par 303 Page 22 FIGURE 3-2. SURFACE CORROSION ON AN AVIONICS MOUNTING RACK
Par 303 Page 23 FIGURE 3-3. CORROSION AND LINT ACCUMULATION ON CARGO DOOR
MICRO-SWITCH
Par 303 Page 24 TABLE 3-1. EFFECTS OF CORROSION ON AVIONICS EQUIPMENT Component Failure Mode Antenna systems Short circuits or changes in circuit constants and structural deterioration.
Chassis, housings, covers, and mount frames Contamination, pitting, loss of finish, and structural deterioration.
Shock mounts and supports Deterioration and loss of shock damping effectiveness.
Control box mechanical and electrical tuning linkage, and motor contacts Intermittent operation and faulty frequency selection.
Water traps Structural deterioration.
Relays and switching systems Mechanical failure, short circuits, intermittent operation, and signal loss.
Plugs, connectors, jacks, and receptacles Short circuits, increasing resistance, intermittent operation, and reduced system reliability.
Multipin cable connectors Short circuits, increasing resistance, intermittent operation, and water seal deterioration.
Power cables Disintegration of insulation and wire/connector deterioration.
Display lamps and wing lights Intermittent operation, mechanical and electrical failures.
Wave guides Loss of integrity against moisture, pitting, reduction of efficiency, and structural deterioration.
Fluid cooling system lines Failure of gaskets, pitting, and power loss.
Printed circuits and microminiature circuits Short circuits, increased resistance, and component and system failures.
Batteries High resistance at terminals, failure of electrical contact points, and structural deterioration of mounting. Erroneous cockpit signals.
Busbars Structural and electrical failures.
Coaxial lines Impedance fluctuations, loss of signal, and structural deterioration of connectors.
c. Structural. Structural parts include housing covers, supports, brackets, cabinets, and chassis, which require structural support and equipment protection. Corrosion on these parts should be cleaned and treated, and the protective finish restored to eliminate long-term deterioration. Severe corrosive damage usually results from damage to the protective finish and subsequent attack to the exposed metal. The protective finish is usually damaged from an environmental attack, handling damage, or microbial growth. Figure 3-2 shows surface corrosion on an avionics mounting rack. Severe corrosion damage requiring major repairs should be accomplished by an authorized repair station. Minor corrosion damage and damaged protective coatings are normally repaired by an authorized certificated person.
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d. Electromechanical. Motion is an integral function of electromechanical switches, relays, potentiometers, motors, generators, and synchronous components. Storage or non-operation in certain environments tends to promote corrosion of these devices. The principal causes of malfunction are dust, condensation products, resultant corrosion products (oxides), and organic contaminate films. Failure of these devices does not normally occur during operation.
The friction generated during operation usually keeps the critical surfaces clean enough to permit operation. On the other hand, during non-operations, insulating films form, which prevent startup operation of the equipment.
FIGURE 3-4. CORRODED HARDWARE ON TERMINAL BOARD
e. E lectronics. Moisture and contaminates penetrate electronic equipment, causing many detrimental effects, such as corrosion. In most modern electronic systems, circuit areas have been minimized for faster signal processing and higher density. In addition, integrated circuits use low voltage for operation. This means that most circuit paths are thin, or small in a cross-sectional area, and that individual circuit paths are close together. In these systems, trace amounts of moisture and contaminates may cause systems failures. Table 3-1 lists the typical effects of corrosion on avionics equipment.