Par 1001 Page 181 CHAPTER 10. EMERGENCY ACTION FOR SERIOUS CORROSION OF AVIONICS
EQUIPMENT 1001. GENERAL.
a. This chapter describes emergency corrosion cleaning and treatment procedures to be followed after aircraft or equipment accidents and incidents, particularly those involving exposure to large amounts of saltwater, fire extinguishing agents, industrial pollutants, soot, etc.
Immediate action must be taken to remove, clean, dry, and preserve all affected avionics equipment to reduce corrosion damage. When removal of avionics equipment is impractical, in-place cleaning, drying, and preserving should be accomplished.
b. The emergency action procedures outlined in the beginning of this chapter are normally used by the operator only to prevent further corrosion damage. Equipment that has received initial emergency treatment should be forwarded to an avionics repair station for cleaning, drying, inspection, operational checks, and preservation, or returned to the Original Equipment Manufacturer (OEM) for disposition as described later in this chapter.
1002. EMERGENCY RECLAMATION TEAM.
NOTE: In cases involving aircraft accidents, permission to remove equipment must be obtained from the senior Department of Transportation (DOT) member of the accident investigation team prior to the start of emergency reclamation procedures.
a. Goal of an Emergency Reclamation Team. Each organization that operates, stores, maintains, or repairs avionics equipment should have a team identified to handle emergency reclamation situations. The primary goal of the emergency reclamation team is to accomplish those tasks that are necessary to salvage the affected equipment and perform appropriate corrosion control efforts to minimize damage.
b. Emergency Reclamation Team Organization. An emergency reclamation team should consist of a senior team member whose responsibilities include directing the salvage, removal priority, and corrosion control efforts for the equipment involved. The size and composition of the remainder of the emergency reclamation team will depend upon the urgency of the situation, type of reclamation effort, and the size of the reclamation task.
1003. EMERGENCY PREPARATIONS.
a. Removal Priority. Each organization that operates, stores, maintains, or repairs avionics equipment should publish an instruction that defines the role and purpose of the emergency reclamation team. The instruction should provide general guidelines for the team to accomplish their task in a safe and efficient manner. It should be reviewed by the emergency reclamation team members on a regular basis, and should include a priority list for the removal and reclamation of equipment and a list of all anticipated tools and materials necessary to accomplish the reclamation task. Table 10-1 provides a recommended guide for a priority removal list.
Par 1003 Page 182 TABLE 10-1. PRIORITY GUIDE FOR EMERGENCY REMOVAL OF AVIONICS
EQUIPMENT Priority Type Equipment
1. Avionics Equipment (radios, computers, radar equipment, etc.)
2. Instruments (aircraft instruments, meters, etc.)
3. Electrical Equipment (switches, wiring, indicator light panels, etc.)
4. Miscellaneous Equipment (mounting racks, etc.)
b. Required Tools, Materials, and Equipment. Immediate availability of the necessary corrosion control tools, materials, and equipment will help to significantly reduce additional damage to the affected equipment. In addition to the corrosion control products listed in Appendix 1, other special support equipment that will be useful and should be readily available are:
(1) Dry nitrogen source,
(2) Dry air source,
(3) Vented drying oven (forced air),
(4) Vented drying oven (bulb-type),
(5) Hot air blowers,
(6) Pump, backpack-style, and
(7) Clean empty 55-gallon drums (removable lid).
c. Production Planning. Whenever possible, all salvaged components of the aircraft or equipment should be treated simultaneously. The most experienced personnel on the emergency reclamation team should be assigned to disassemble and process the affected equipment. This effort will reduce the corrosion potential and other damage to the equipment and ensure that the work is accomplished in a thorough and competent manner. Whenever possible, personnel that normally examine and evaluate this type of equipment should work closely with the disassembly and preservation personnel. This enables non-reclaimable items to be scrapped immediately and only usable components that were exposed to corrosive agents to be disassembled and treated.
The time saved by this procedure may be used in preserving salvageable components.
1004. EMERGENCY CLEANING PROCEDURES.
CAUTION: Cleaning compounds and solvents identified in Appendix 1 may react with some encapsulants or plastics used to form wire harness tubing, wire coatings, conformal coatings, gaskets, seals, etc. Test these compounds and solvents on a small area for softening or other adverse reactions prior to
Par 1004 Page 183 general application. See Chapter 4, Table 4-3, for further restrictions on these materials.
a. General. Where possible, the primary method of emergency cleaning described in subparagraph 1004b should be used. When a sufficient quantity of fresh water is not available, use one of the alternate emergency cleaning methods described in subparagraphs 1004c(1) through (3).
b. Primary Method. The primary method for the removal of saltwater, fire extinguishing agents, etc., should be used when a sufficient quantity of fresh water is available. The primary method procedures are:
(1) Flush all internal and external areas with clean fresh water. Whenever possible, units or subcomponents that have been removed should be immersed and flushed thoroughly in clean fresh water. A 55-gallon drum may be used for this purpose. Tilt the unit or subcomponent back and forth to aid in draining off the excess water.
(2) Blow off excess water with not more than 10 pounds per square inch (psi) air pressure or dry nitrogen. Deflect jet of air off interior, back, and sides of enclosure to diffuse.
(3) If there is any evidence of salt or fire extinguishing agents, a second cleaning action should be initiated using a solution of 1 part Aircraft Cleaning Compound to 10 parts of fresh water, conforming to MIL-PRF-85570, Type II. Scrub the affected areas with the cleaning solution using a brush. Flush thoroughly with fresh water and drain excess. The equipment may be immersed in fresh water to aid in removing hidden contaminants. Tilt the unit or equipment back and forth to aid in draining off the excess water.
(4) Blow off excess water as specified in subparagraph 1004b(2).
c. Alternate Methods. The following describes alternate cleaning methods when sufficient fresh water is not available.
(1) Solvent Method.
NOTE: Local air pollution regulations may restrict the use of this and other solvents. Comply with all local air pollution regulations.
(a) Clean exterior of equipment using a brush and dry cleaning solvent, MIL-PRF-680, Type II.
(b) Collect waste solvent from exterior cleaning and dispose of by recycling or as a hazardous waste.
CAUTION: Properly dispose of all hazardous waste in accordance with local regulations.
(c) Disassemble equipment as required. Clean and dry interior surfaces in accordance with instructions of subparagraphs 1004b(3) and (4).
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(2) Aircraft Cleaning Compound Method.
(a) Apply a solution of 1 part Aircraft Cleaning Compound to 9 parts of fresh water, conforming to MIL-PRF-85570, Type I. Scrub or wipe interior and exterior surfaces of equipment using a brush or clean cloth until contaminants become intermixed or emulsified.
Wipe off all surfaces thoroughly with a clean cloth removing contaminants and cleaner.
(b) Blow off excess solution with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(3) Water-Displacing Method. The water-displacing method should be used as the last choice of the alternate cleaning methods. Additionally, the water-displacing method is considered only temporary preservation until proper cleaning methods can be accomplished.
After application of the water-displacing compound, tag equipment with an appropriate marking indicating the component has been temporarily preserved with Water-Displacing Corrosion Preventive Compound, conforming to MIL-PRF-81309, Type II, but still requires cleaning.
(a) Blow off excess water and other contaminants from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Totally immerse equipment in a 55-gallon drum of Water-Displacing Corrosion Preventive Compound, conforming to MIL-PRF-81309, Type II. Tilt the unit or equipment back and forth to aid in removing any water. Immerse the equipment a second time, repeating the tilting to thoroughly coat all surfaces. If total immersion is not practical, spray, brush, or wipe the interior and exterior of equipment with Water-Displacing Corrosion Preventive Compound.
(c) Blow off excess Water-Displacing Corrosion Preventive Compound from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
1005. EMERGENCY DRYING AND PRESERVATION.
a. General. Drying and preservation are essential to eliminate any traces of water and to control corrosion until the equipment can be disassembled, inspected, and repaired at an authorized repair station.
b. Drying and Preservation Procedures. The following drying and preservation procedures should be used with the listed drying equipment after cleaning in accordance with subparagraph 1004b.
(1) Vented Drying Oven (Forced Air).
(a) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Dry the equipment in a vented forced air oven at a temperature of not more than 130 °F (54 °C) for 1 to 2 hours.
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(c) For all avionics components and electrical connectors, apply (by spraying) a coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
(2) Vacuum Oven Drying.
(a) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Dry the equipment in a vacuum oven with a temperature of not more than 130 °F (54 °C) and a minimum pressure of 25 inches of Hg (inHg) for 1 to 2 hours.
(c) For all avionics components and electrical connectors, apply (by spraying) a coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
(3) Vented Drying Oven (Bulb-Type).
(a) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Dry the equipment in a vented bulb-type drying oven at not more than 130 °F (54 °C) for 4 to 6 hours.
(c) For all avionics components and electrical connectors, apply (by spraying) a coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
(4) Hot Air Blower.
(a) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Dry the equipment with a hot air blower until dry.
(c) For all avionics components and electrical connectors, apply (by spraying) a coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
(5) Heated Compartment.
(a) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(b) Dry the equipment in a heated compartment with proper air circulation at a temperature between 100 °F (38 °C) and 130 °F (54 °C) until dry.
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(c) For all avionics components and electrical connectors, apply (by spraying) a coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
1006. OPERATOR LEVEL EMERGENCY CLEANING PROCEDURES.
WARNING: Ensure that all electrical power internal and external to the aircraft or equipment is disconnected. Disconnect all batteries. Ensure that all safety devices are installed.
a. Removable Avionics Equipment. Equipment or components that are removed at the operator’s facility should be inspected for smoke, heat, fire damage, or damaged seals.
Equipment and components that are forwarded to the operator’s facility should have their background researched to determine the extent, cause of damage, and previous cleaning and preservation procedures that may have been accomplished. Most avionics equipment contain dissimilar metals and particular attention should be paid to these areas for evidence of corrosion during the inspection. If contaminated avionics equipment can be forwarded immediately and inducted into an avionics repair station for expeditious cleaning, inspection, and repair of damage, then the drying and preservation identified in paragraph 1005 is not necessary. When immediate induction into the avionics repair station is not possible, proceed with the drying and preservation procedures of paragraph 1005. When the aircraft or equipment has been exposed to saltwater intrusion, fire extinguishing agents, or water immersion, the aircraft or equipment should be cleaned, dried, and preserved as follows:
(1) Electrically ground the aircraft or equipment.
WARNING: Ensure that all electrical power sources, including batteries, are disconnected from the aircraft or equipment and all other powered systems (hydraulic, pneumatic, and mechanical) are deactivated.
(2) Ensure all external electrical power and batteries are disconnected. Remove hydraulic and pneumatic power and install safety struts in hydraulic, pneumatic, and mechanic actuated devices.
(3) Remove installed avionics equipment. Removal priority should be determined from the developed priority list for emergency reclamation of equipment or as directed by the emergency reclamation team leader. See paragraph 1003 and Table 10-1.
(4) Remove all covers, modules, and components authorized at this level.
(5) Tilt the equipment back and forth to allow accumulated water or other liquids to drain off.
(6) Examine the individual items thoroughly for evidence of saltwater, fire extinguishing agents, smoke, oily films, corrosion, etc.
(7) Items that are contaminated should be cleaned using the primary cleaning method described in subparagraph 1004b.
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(8) If the primary method cannot be performed for lack of available fresh water, use one of the alternate cleaning methods described in subparagraph 1004c.
(9) Tag all components, identifying date, cleaning and drying method, and type of preservation applied.
b. Removal and Cleaning of Identification and Modification Plates. Identification and modification plates can trap contaminants, allowing corrosion to start. The following procedures are applicable for the cleaning of identification and modification plates:
(1) Visually examine for the presence and the condition of a fillet seal along the edge of the identification and modification plates. Identification and modification plates with sealed edges that appear intact and undamaged do not have to be removed at this maintenance level.
Identification and modification plates with missing or damaged edge seals should be removed.
(2) Remove the affected identification and modification plate as required.
(3) Thoroughly clean both sides of the identification and modification plate and the adjacent mounting areas on the equipment using the primary cleaning method described in subparagraph 1004b.
(4) Installation of the identification and modification plates will depend on any additional processing of the avionics component at another level of maintenance. To maintain correct identity and configuration control, reinstall the identification and modification plates. If the avionics component will be repaired at the operator level and returned to service, proceed as follows:
(a) Visually examine the identification and modification plate and the adjacent mounting areas for evidence of corrosion. Clean, treat, and reapply any protective finish in accordance with Chapter 4, paragraph 405, and Chapter 5, paragraphs 502, 503, and 504, as required.
(b) After cleaning and surface treatment, lightly coat the seal by applying a coating of Sealing Compound to the underside of the identification and modification plate and the adjacent mounting areas, conforming to SAE-AMS-S-8802. Install identification and modification plate within the working time of the sealant. Ensure sealant squeezes out around the periphery of the plate.
c. Hermetically Sealed Avionics Equipment. When removing hermetically sealed units, pay particular attention to cable clamp areas, bindings securing wire harnesses, and cable connectors. These are areas where salt and fire extinguishing agents can become entrapped.
Immerse the unit in a container of fresh water to test for airtight integrity of the seal. The presence of air bubbles will indicate a faulty seal. Clean hermetically sealed avionics equipment as follows:
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(1) Clean the equipment in accordance with subparagraph 1004b or c.
(2) Dry and preserve the equipment in accordance with one of the methods described in subparagraph 1005b.
(3) Units that indicate a faulty seal should be forwarded to an avionics repair station for disposition.
d. Electric Motors and Generators. Cleaning is an essential preliminary procedure in salvaging electric motors, generators, inverters, and miniature synchro transmitters and receivers.
(1) Clean the equipment in accordance with subparagraph 1004b or c.
(2) Dry and preserve the equipment in accordance with one of the methods described in subparagraph 1005b.
(3) Thoroughly inspect the equipment to determine whether it may be returned to serviceable condition or must be forwarded to an avionics repair station. Equipment with sealed bearings should be forwarded to an avionics repair station for replacement.
(4) Equipment that is determined serviceable should have the Corrosion Preventive Compound removed using Dry Cleaning Solvent, MIL-PRF-680, Type II.
(5) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back and sides of enclosure to disuse.
e. Cockpit Area Components. The cockpit area contains various types of components.
Non-removable components and equipment should be cleaned, dried, and preserved in accordance with subparagraphs 1006i through 1006k. Removable components should be cleaned and preserved as follows:
(1) Remove all removable components, control boxes, equipment, relay boxes, indicators, etc., in accordance with the OEM maintenance instructions.
(2) Visually examine all removed components for evidence of saltwater, fire extinguishing agents, smoke, oily films, etc.
(3) Clean contaminated equipment in accordance with subparagraph 1004b.
(4) Dry and preserved the equipment in accordance with subparagraph 1005b.
(5) Special attention should be given to cockpit electrical connectors. Clean and preserve in accordance with subparagraph 1006m.
(6) Cockpit circuit breakers, toggle, rotary, interlock, and push-button switches should be cleaned and preserved in accordance with subparagraph 1006f.
f. Switches and Circuit Breakers. Most aircraft and aircraft-related test equipment switches are enclosed in a sealed case. Cleaning of internal parts is generally not possible.
Par 1006 Page 189 Exposed areas such as terminal posts, toggles, push buttons, or rotary switches should be cleaned and preserved as follows:
(1) Remove contamination with fresh water while scrubbing with an acid brush.
Thoroughly rinse with fresh water.
(2) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Wipe with a clean cloth to help reduce drying time.
(3) Use Dry Cleaning Solvent, MIL-PRF-680, Type II, applied with an acid brush, to remove stubborn oil and grease stains and clean sliding contacts, contact points, and circuit breaker points. Rinse with Dry Cleaning Solvent, MIL-PRF-680, Type II. Ensure removal of any contamination from sliding contacts, contact points, and circuit breaker points. Wipe with a clean cloth.
(4) Dry in accordance with one of the methods described in subparagraph 1005b. Do not apply Water-Displacing Corrosion Preventive Compounds as directed in that paragraph.
(5) If required, preserve exterior of switch in accordance with Chapter 4, paragraph 407.
g. Antennas. Antennas should be cleaned and preserved as follows:
(1) Remove the antenna in accordance with OEM maintenance instructions.
(2) Visually examine antennas, insulators, and electrical connectors for damage. Repair or replace as required.
(3) Brush or spray a mixture of one part Aircraft Cleaning Compound conforming to MIL-PRF-85570, Type I, to nine parts of fresh water. Clean surfaces with a clean cloth dampened with cleaning solution.
(4) Rinse with clean fresh water. Wipe excess water with a dry, clean cloth.
(5) Preserve antenna in accordance with Chapter 4, paragraph 407.
h. Mounting Racks and Shock Mounts. Mounting racks and shock mounts should be cleaned and preserved as follows:
(1) Remove the mounting racks, shock mounts, and associated hardware in accordance with the OEM maintenance instructions.
(2) Clean the detailed parts or components in accordance with subparagraph 1004b.
(3) Dry the mounting racks, shock mounts, and associated hardware in accordance with one of the methods described in subparagraph 1005b.
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(4) Tag the equipment to be forwarded to the avionics repair station. The tag should indicate date, cleaning and drying method, and preservation type applied. Include any additional notes that may be helpful.
i. Non-removable Avionics Equipment. Non-removable avionics equipment exposed to saltwater or fire extinguishing agents should be cleaned and preserved as follows:
(1) Ensure aircraft or equipment is electrically grounded.
WARNING: Ensure that all electrical power sources, including batteries, are disconnected from the aircraft or equipment and all other powered systems (hydraulic, pneumatic, and mechanical) are deactivated.
(2) Ensure all external electrical power and batteries are disconnected. Remove hydraulic and pneumatic power and install safety struts in hydraulic, pneumatic, and mechanic actuated devices.
(3) Open all equipment bay doors.
(4) After all removable components have been removed in accordance with the OEM maintenance instructions and in the order determined by the priority established in the emergency reclamation list or Table 10-1, examine all non-removable components for evidence of saltwater, fire extinguishing agents, smoke, oily films, etc.
(5) Contaminated items should be cleaned in accordance with subparagraph 1004b whenever possible. Ensure that areas behind and under mounting structure and components are thoroughly cleaned. When the primary cleaning method cannot be accomplished, use one of the alternate cleaning methods described in subparagraph 1004c.
(6) For all non-removable avionics components and electrical connectors, dry and preserve in accordance with subparagraph 1006k.
j. In-place Cleaning. Where access is limited, use a backpack hand pump for one of the cleaning methods described in subparagraph 1004c, except the solvent method described in subparagraph 1004c(1). Dry and preserve limited-access components in accordance with subparagraph 1006k.
k. Drying and Preservation of Non-removable Avionics Equipment. Dry and preserve non-removable avionics components as follows:
(1) Blow off excess liquid from component with not more than 10 psi dry air pressure or dry nitrogen. Deflect the jet of air off interior, back, and sides of enclosure to diffuse.
(2) Where authorized, dry the equipment with a hot air gun. Where the hot air gun is not authorized, wipe the area with a dry, clean cloth and allow to air dry.
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(3) For all avionics components and electrical connectors, apply (by spraying) a coat of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III. Wipe off excess preservative with a dry, clean cloth.
l. Terminal Boards, Junction Boxes, Relay Boxes, and Circuit Breaker Panels.
Terminal boards, junction boxes, relay boxes, and circuit breaker panels not normally removed from the aircraft or equipment should be cleaned as follows:
(1) Ensure aircraft or equipment is electrically grounded.
WARNING: Ensure that all electrical power sources, including batteries, are disconnected from the aircraft or equipment and all other powered systems (hydraulic, pneumatic, and mechanical) are deactivated.
(2) Ensure all external electrical power and batteries are disconnected. Remove hydraulic and pneumatic power, and install safety struts in hydraulic, pneumatic, and mechanic actuated devices.
(3) Remove covers and access panels.
(4) Examine all components for evidence of saltwater, fire extinguishing agents, smoke, oily films, etc.
(5) Contaminated components should be cleaned in accordance with the primary cleaning method described in subparagraph 1004b whenever possible. Ensure that all areas behind and under mounting structure and components are thoroughly cleaned. When the primary cleaning method cannot be accomplished, use one of the alternate cleaning methods described in subparagraph 1004c.
(6) For all non-removable avionics components and electrical connectors, dry and preserve in accordance with subparagraph 1006k.
m. Electrical Connectors and Receptacles. Electrical connectors and receptacles require special procedures for cleaning and preserving. Connectors and receptacles that cannot be opened and separated for cleaning should be cleaned, inspected, and preserved in place as follows:
(1) Disconnect and disassemble connector and receptacles to the extent possible to release entrapped contaminants.
(2) Thoroughly rinse connector and receptacles with fresh water.
(3) Blow off excess liquid from connector and receptacles with not more than 10 psi dry air pressure or dry nitrogen. Wipe with a clean cloth to help reduce drying time.
(4) To remove stubborn oil and grease contaminants, use Dry Cleaning Solvent, MIL-PRF-680, Type II, applied with an acid brush, followed by wiping with a solvent-dampened cleaning cloth.
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(5) Apply (by spraying) a light coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III, to remove any trapped liquid. Wipe off excess preservative with a dry, clean cloth.
(6) Dry and preserve in accordance with one of the methods described in subparagraphs 1005b(1) through (5). Whenever these drying methods are not applicable, allow connector to air dry.
n. Wire Harnesses and Cables. Wire harnesses and cables exposed to saltwater, fire extinguishing agents, smoke, etc., should be cleaned and preserved as follows:
(1) Remove cable clamps, straps, hangers, wire ties, etc., to allow wire harness and cable wiring to be separated.
(2) Separate wiring, open and separate connectors. Rinse with fresh water to wash away entrapped contaminants. If the wire harness, cables, or connectors are encased, the exteriors should be rinsed with fresh water.
(3) Blow excess water from wiring and connectors with not more than 10 psi dry air pressure or dry nitrogen. Wipe with a clean cloth to help reduce drying time.
(4) Wire harnesses and cables that can be readily removed from the aircraft or equipment should be dried by one of the methods in subparagraph 1005b.
(5) Wire harnesses and cables that cannot be readily removed from the aircraft or equipment should be dried using a hot air gun.
(6) Apply (by spraying) to metal components a light coating of Water-Displacing Corrosion Preventive Compound, Ultra-Thin Film, conforming to MIL-PRF-81309, Type III.
1007. AVIONICS REPAIR STATION EMERGENCY CLEANING PROCEDURES.
a. General. The initial emergency salvage and reclamation steps taken by the operator or unit level are designed to prevent further corrosion damage. Immediate induction of avionics equipment into an avionics repair station for cleaning, drying, inspection, preservation, repair, and functional testing after an accident can be delayed for many reasons. These can include the delayed access due to an ongoing accident investigation, field disassembly problems, shipping distance, and work contracts. It is, therefore, essential that the avionics repair station be ready to provide services when the equipment does arrive.
b. Emergency Reclamation Team. Each avionics repair station that operates, stores, maintains, or repairs avionics equipment should have a team identified to handle emergency reclamation situations. The team should be composed of a team leader and the necessary number of avionics technicians required to accomplish the assigned task. The primary goal of the emergency reclamation team is to accomplish those tasks that are necessary to salvage the affected equipment and perform appropriate corrosion control efforts to minimize damage and, where possible, return the equipment to usable service. Repairable equipment damaged beyond the capability of the avionics repair station may be returned to the OEM for disposition.